Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Reynolds number: 500,000 Max Cl/Cd: 102.47 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-prandtl-d-root-ns-500000.txt Download as CSV file: xf-prandtl-d-root-ns-500000.csv |
XFOIL Version 6.96
Calculated polar for: Prandtl-D root - NASA Preliminary Research Aerod
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-20.000 -0.5453 0.23479 0.23317 0.0646 1.0000 0.0087
-19.750 -0.5381 0.23154 0.22992 0.0625 1.0000 0.0089
-19.500 -0.5309 0.22821 0.22659 0.0603 1.0000 0.0094
-19.250 -0.5236 0.22486 0.22323 0.0582 1.0000 0.0097
-19.000 -0.5165 0.22133 0.21969 0.0559 1.0000 0.0103
-18.750 -0.5101 0.21769 0.21605 0.0534 1.0000 0.0106
-18.500 -0.5036 0.21437 0.21273 0.0509 1.0000 0.0107
-18.250 -0.4995 0.21107 0.20942 0.0480 1.0000 0.0108
-18.000 -0.4916 0.20704 0.20540 0.0462 1.0000 0.0109
-17.750 -0.4832 0.20405 0.20239 0.0442 0.9822 0.0110
-17.500 -0.4881 0.20416 0.20248 0.0472 0.9520 0.0111
-17.250 -0.4881 0.20273 0.20102 0.0480 0.9421 0.0113
-17.000 -0.4836 0.20049 0.19877 0.0472 0.9355 0.0116
-16.750 -0.4808 0.19837 0.19663 0.0468 0.9293 0.0118
-16.500 -0.4750 0.19567 0.19392 0.0454 0.9245 0.0123
-16.250 -0.4707 0.19310 0.19132 0.0443 0.9196 0.0129
-16.000 -0.4662 0.19028 0.18848 0.0430 0.9152 0.0136
-15.750 -0.4621 0.18712 0.18531 0.0406 0.9115 0.0140
-15.500 -0.4603 0.18425 0.18243 0.0383 0.9079 0.0141
-15.250 -0.4586 0.18157 0.17973 0.0364 0.9044 0.0142
-15.000 -0.4553 0.17861 0.17676 0.0343 0.9009 0.0142
-14.750 -0.4437 0.17484 0.17296 0.0342 0.8952 0.0146
-14.500 -0.4376 0.17237 0.17047 0.0332 0.8908 0.0147
-14.250 -0.4307 0.16995 0.16802 0.0320 0.8863 0.0150
-14.000 -0.4240 0.16737 0.16543 0.0305 0.8816 0.0155
-13.750 -0.4186 0.16477 0.16281 0.0290 0.8774 0.0158
-13.500 -0.4137 0.16214 0.16015 0.0276 0.8736 0.0164
-13.250 -0.4080 0.15922 0.15722 0.0256 0.8695 0.0171
-13.000 -0.4067 0.15595 0.15393 0.0228 0.8668 0.0182
-12.750 -0.4081 0.15315 0.15112 0.0197 0.8647 0.0184
-12.500 -0.4084 0.15050 0.14845 0.0172 0.8629 0.0185
-12.250 -0.4077 0.14687 0.14480 0.0154 0.8611 0.0187
-12.000 -0.3978 0.14413 0.14204 0.0149 0.8556 0.0190
-11.750 -0.3901 0.14147 0.13936 0.0139 0.8501 0.0193
-11.500 -0.3841 0.13874 0.13658 0.0127 0.8453 0.0197
-11.250 -0.4486 0.13440 0.13225 0.0019 0.9190 0.0193
-11.000 -0.4429 0.13136 0.12918 0.0010 0.9092 0.0195
-10.750 -0.4370 0.12846 0.12623 0.0003 0.9001 0.0201
-10.500 -0.4326 0.12506 0.12281 -0.0010 0.8916 0.0205
-10.250 -0.4283 0.12152 0.11925 -0.0024 0.8833 0.0209
-10.000 -0.4259 0.11772 0.11542 -0.0040 0.8752 0.0218
-9.750 -0.4288 0.11241 0.11011 -0.0074 0.8671 0.0232
-9.500 -0.4288 0.10800 0.10566 -0.0097 0.8594 0.0235
-9.250 -0.4289 0.10318 0.10085 -0.0125 0.8506 0.0237
-9.000 -0.4404 0.09618 0.09384 -0.0156 0.8438 0.0241
-8.750 -0.4391 0.09246 0.09011 -0.0169 0.8344 0.0244
-8.500 -0.4312 0.09059 0.08821 -0.0170 0.8253 0.0249
-8.250 -0.4310 0.08685 0.08444 -0.0187 0.8160 0.0251
-8.000 -0.4271 0.08409 0.08166 -0.0197 0.8065 0.0258
-7.750 -0.4288 0.08038 0.07792 -0.0216 0.7977 0.0263
-7.500 -0.4353 0.07593 0.07347 -0.0242 0.7879 0.0266
-7.250 -0.5802 0.04035 0.03706 -0.0389 0.7811 0.0192
-7.000 -0.5751 0.03623 0.03269 -0.0376 0.7732 0.0173
-6.750 -0.5798 0.03012 0.02590 -0.0352 0.7668 0.0166
-6.500 -0.5715 0.02602 0.02124 -0.0331 0.7592 0.0163
-6.250 -0.5548 0.02376 0.01856 -0.0316 0.7529 0.0166
-6.000 -0.5344 0.02202 0.01651 -0.0305 0.7457 0.0170
-5.750 -0.5123 0.02074 0.01494 -0.0296 0.7393 0.0176
-5.500 -0.4893 0.01942 0.01334 -0.0287 0.7328 0.0180
-5.250 -0.4650 0.01842 0.01210 -0.0279 0.7264 0.0183
-5.000 -0.4422 0.01688 0.01030 -0.0270 0.7209 0.0188
-4.750 -0.4189 0.01551 0.00883 -0.0262 0.7148 0.0197
-4.500 -0.3939 0.01479 0.00801 -0.0256 0.7092 0.0206
-4.250 -0.3683 0.01418 0.00730 -0.0251 0.7036 0.0217
-4.000 -0.3421 0.01367 0.00671 -0.0247 0.6978 0.0230
-3.750 -0.3170 0.01304 0.00594 -0.0241 0.6929 0.0246
-3.500 -0.2915 0.01244 0.00531 -0.0236 0.6877 0.0267
-3.250 -0.2649 0.01204 0.00484 -0.0232 0.6823 0.0289
-3.000 -0.2387 0.01164 0.00434 -0.0228 0.6776 0.0322
-2.750 -0.2115 0.01133 0.00406 -0.0226 0.6727 0.0383
-2.500 -0.1845 0.01098 0.00376 -0.0223 0.6677 0.0548
-2.250 -0.1575 0.01076 0.00352 -0.0221 0.6632 0.0697
-2.000 -0.1300 0.01059 0.00336 -0.0220 0.6585 0.0820
-1.750 -0.1024 0.01039 0.00319 -0.0219 0.6536 0.0941
-1.500 -0.0752 0.01021 0.00301 -0.0217 0.6492 0.1095
-1.250 -0.0482 0.01000 0.00286 -0.0216 0.6449 0.1369
-1.000 -0.0212 0.00972 0.00274 -0.0215 0.6402 0.1773
-0.750 0.0056 0.00947 0.00263 -0.0213 0.6359 0.2242
-0.500 0.0318 0.00923 0.00254 -0.0211 0.6319 0.2838
-0.250 0.0583 0.00897 0.00248 -0.0209 0.6276 0.3449
0.000 0.0844 0.00870 0.00243 -0.0206 0.6231 0.4125
0.250 0.1092 0.00841 0.00237 -0.0200 0.6192 0.4964
0.750 0.2088 0.00735 0.00267 -0.0288 0.6107 0.9438
1.000 0.2459 0.00757 0.00282 -0.0304 0.6062 0.9654
1.250 0.3000 0.00780 0.00293 -0.0358 0.6022 0.9790
1.500 0.3607 0.00792 0.00298 -0.0428 0.5976 0.9905
1.750 0.4227 0.00782 0.00282 -0.0501 0.5927 1.0000
2.000 0.4495 0.00786 0.00280 -0.0499 0.5887 1.0000
2.250 0.4763 0.00793 0.00281 -0.0498 0.5848 1.0000
2.500 0.5034 0.00795 0.00283 -0.0497 0.5803 1.0000
2.750 0.5303 0.00798 0.00283 -0.0496 0.5760 1.0000
3.000 0.5571 0.00805 0.00284 -0.0494 0.5720 1.0000
3.250 0.5841 0.00810 0.00289 -0.0493 0.5676 1.0000
3.500 0.6111 0.00813 0.00293 -0.0492 0.5627 1.0000
3.750 0.6379 0.00819 0.00295 -0.0490 0.5580 1.0000
4.000 0.6647 0.00825 0.00301 -0.0489 0.5531 1.0000
4.250 0.6917 0.00829 0.00307 -0.0488 0.5478 1.0000
4.500 0.7182 0.00836 0.00307 -0.0486 0.5413 1.0000
4.750 0.7451 0.00837 0.00315 -0.0485 0.5341 1.0000
5.000 0.7716 0.00841 0.00314 -0.0483 0.5242 1.0000
5.250 0.7981 0.00844 0.00316 -0.0481 0.5126 1.0000
5.500 0.8246 0.00848 0.00322 -0.0480 0.5005 1.0000
5.750 0.8510 0.00856 0.00328 -0.0478 0.4864 1.0000
6.000 0.8769 0.00869 0.00335 -0.0476 0.4680 1.0000
6.250 0.9029 0.00884 0.00347 -0.0475 0.4487 1.0000
6.500 0.9284 0.00906 0.00362 -0.0473 0.4257 1.0000
6.750 0.9532 0.00936 0.00383 -0.0470 0.3971 1.0000
7.000 0.9762 0.00991 0.00416 -0.0467 0.3496 1.0000
7.250 0.9952 0.01096 0.00480 -0.0461 0.2727 1.0000
7.500 1.0120 0.01208 0.00554 -0.0451 0.2058 1.0000
7.750 1.0267 0.01323 0.00634 -0.0438 0.1440 1.0000
8.000 1.0386 0.01442 0.00719 -0.0420 0.0889 1.0000
8.250 1.0491 0.01553 0.00804 -0.0399 0.0474 1.0000
8.500 1.0650 0.01609 0.00859 -0.0383 0.0392 1.0000
8.750 1.0799 0.01665 0.00915 -0.0365 0.0325 1.0000
9.250 1.0993 0.01810 0.01053 -0.0314 0.0141 1.0000
9.500 1.1054 0.01872 0.01119 -0.0283 0.0135 1.0000
9.750 1.1047 0.01940 0.01193 -0.0242 0.0128 1.0000
10.000 1.1079 0.02019 0.01279 -0.0209 0.0122 1.0000
10.250 1.1139 0.02103 0.01369 -0.0183 0.0120 1.0000
10.500 1.1210 0.02194 0.01466 -0.0161 0.0118 1.0000
10.750 1.1281 0.02295 0.01574 -0.0141 0.0117 1.0000
11.000 1.1359 0.02401 0.01686 -0.0123 0.0117 1.0000
11.250 1.1427 0.02523 0.01816 -0.0106 0.0115 1.0000
11.500 1.1487 0.02659 0.01961 -0.0090 0.0114 1.0000
11.750 1.1545 0.02803 0.02112 -0.0076 0.0113 1.0000
12.000 1.1586 0.02970 0.02287 -0.0062 0.0110 1.0000
12.250 1.1635 0.03135 0.02459 -0.0050 0.0110 1.0000
12.500 1.1658 0.03328 0.02659 -0.0038 0.0106 1.0000
12.750 1.1699 0.03511 0.02849 -0.0028 0.0106 1.0000
13.000 1.1707 0.03729 0.03075 -0.0018 0.0105 1.0000
13.250 1.1728 0.03940 0.03294 -0.0010 0.0105 1.0000
13.500 1.1743 0.04161 0.03523 -0.0002 0.0105 1.0000
13.750 1.1756 0.04390 0.03760 0.0004 0.0104 1.0000
14.000 1.1757 0.04641 0.04019 0.0010 0.0104 1.0000
14.250 1.1773 0.04879 0.04263 0.0015 0.0103 1.0000
14.500 1.1793 0.05119 0.04510 0.0019 0.0103 1.0000
14.750 1.1802 0.05373 0.04771 0.0024 0.0103 1.0000
15.000 1.1826 0.05613 0.05019 0.0027 0.0103 1.0000
15.250 1.1846 0.05859 0.05272 0.0031 0.0103 1.0000
15.500 1.1859 0.06112 0.05531 0.0035 0.0101 1.0000
15.750 1.1899 0.06340 0.05768 0.0040 0.0102 1.0000
16.000 1.1928 0.06577 0.06013 0.0044 0.0101 1.0000
16.250 1.1974 0.06803 0.06249 0.0047 0.0103 1.0000
16.500 1.2019 0.07029 0.06486 0.0052 0.0105 1.0000
16.750 1.2050 0.07277 0.06746 0.0056 0.0105 1.0000
17.000 1.2082 0.07530 0.07013 0.0060 0.0109 1.0000
17.250 1.2101 0.07800 0.07296 0.0063 0.0110 1.0000
17.500 1.2099 0.08111 0.07620 0.0064 0.0110 1.0000
17.750 1.2103 0.08405 0.07930 0.0072 0.0116 1.0000
18.000 1.2062 0.08790 0.08330 0.0063 0.0115 1.0000
18.250 1.2009 0.09200 0.08755 0.0055 0.0115 1.0000
18.500 1.1931 0.09661 0.09232 0.0043 0.0116 1.0000
18.750 1.2058 0.09773 0.09346 0.0061 0.0124 1.0000
19.000 1.1953 0.10310 0.09904 0.0035 0.0126 1.0000
19.250 0.9727 0.10874 0.10525 0.0054 0.0121 1.0000
19.500 0.9618 0.11290 0.10953 0.0028 0.0122 1.0000
19.750 0.9492 0.11746 0.11423 -0.0002 0.0123 1.0000
20.000 0.9367 0.12226 0.11917 -0.0034 0.0123 1.0000
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