Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag (prandtl-d-root-ns) Reynolds number: 1,000,000 Max Cl/Cd: 117.94 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-prandtl-d-root-ns-1000000.txt Download as CSV file: xf-prandtl-d-root-ns-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-20.000 -0.7396 0.26002 0.25846 0.0801 1.0000 0.0056
-19.750 -0.7310 0.25633 0.25477 0.0776 1.0000 0.0056
-19.500 -0.7225 0.25290 0.25135 0.0752 1.0000 0.0056
-19.250 -0.7142 0.24930 0.24775 0.0727 1.0000 0.0056
-19.000 -0.7057 0.24590 0.24435 0.0703 1.0000 0.0057
-18.750 -0.6969 0.24218 0.24064 0.0685 1.0000 0.0057
-18.500 -0.6874 0.23952 0.23798 0.0667 1.0000 0.0059
-18.250 -0.6782 0.23660 0.23506 0.0646 1.0000 0.0060
-18.000 -0.6690 0.23345 0.23191 0.0625 1.0000 0.0060
-17.750 -0.6596 0.23062 0.22909 0.0604 1.0000 0.0063
-17.500 -0.6504 0.22738 0.22585 0.0583 1.0000 0.0064
-17.250 -0.6412 0.22415 0.22261 0.0561 1.0000 0.0068
-17.000 -0.6322 0.22074 0.21921 0.0540 1.0000 0.0071
-16.750 -0.6236 0.21631 0.21478 0.0514 1.0000 0.0078
-16.500 -0.6158 0.21235 0.21083 0.0488 1.0000 0.0079
-16.250 -0.6081 0.20850 0.20699 0.0463 1.0000 0.0079
-16.000 -0.5998 0.20474 0.20323 0.0439 1.0000 0.0080
-15.750 -0.5916 0.20089 0.19939 0.0416 1.0000 0.0080
-15.500 -0.5837 0.19669 0.19519 0.0398 1.0000 0.0081
-15.250 -0.5736 0.19380 0.19230 0.0381 1.0000 0.0082
-15.000 -0.5641 0.19076 0.18927 0.0363 1.0000 0.0084
-14.750 -0.5549 0.18752 0.18603 0.0342 1.0000 0.0085
-14.500 -0.5457 0.18425 0.18277 0.0322 1.0000 0.0087
-14.250 -0.5357 0.18075 0.17924 0.0296 0.9599 0.0090
-14.000 -0.5279 0.17735 0.17576 0.0278 0.9352 0.0091
-13.750 -0.5218 0.17395 0.17232 0.0264 0.9233 0.0096
-13.500 -0.5159 0.17008 0.16841 0.0248 0.9147 0.0102
-13.250 -0.5143 0.16445 0.16276 0.0216 0.9075 0.0107
-13.000 -0.4333 0.15428 0.15258 0.0281 0.8201 0.0110
-12.750 -0.4269 0.15181 0.15008 0.0265 0.8158 0.0111
-12.500 -0.4197 0.14974 0.14799 0.0250 0.8113 0.0113
-12.250 -0.4152 0.14761 0.14583 0.0232 0.8078 0.0114
-12.000 -0.4104 0.14504 0.14325 0.0212 0.8035 0.0116
-11.750 -0.4048 0.14204 0.14020 0.0194 0.7983 0.0118
-11.500 -0.3995 0.13875 0.13689 0.0175 0.7931 0.0121
-11.250 -0.3945 0.13524 0.13335 0.0155 0.7874 0.0124
-11.000 -0.3904 0.13143 0.12951 0.0134 0.7825 0.0130
-10.750 -0.3920 0.12566 0.12374 0.0101 0.7791 0.0140
-10.500 -0.3895 0.12110 0.11916 0.0077 0.7738 0.0141
-10.250 -0.3877 0.11625 0.11428 0.0054 0.7689 0.0142
-10.000 -0.3867 0.11129 0.10931 0.0032 0.7642 0.0142
-9.750 -0.3870 0.10591 0.10391 0.0008 0.7593 0.0142
-9.500 -0.8056 0.03599 0.03326 -0.0387 0.8093 0.0085
-9.250 -0.8046 0.03311 0.03011 -0.0372 0.7999 0.0086
-9.000 -0.7886 0.03204 0.02893 -0.0364 0.7911 0.0088
-8.750 -0.7823 0.02933 0.02591 -0.0348 0.7824 0.0089
-8.500 -0.7659 0.02797 0.02439 -0.0338 0.7733 0.0091
-8.250 -0.7530 0.02587 0.02200 -0.0324 0.7650 0.0092
-8.000 -0.7358 0.02433 0.02023 -0.0313 0.7564 0.0094
-7.750 -0.7179 0.02278 0.01843 -0.0302 0.7486 0.0096
-7.500 -0.6990 0.02129 0.01670 -0.0291 0.7405 0.0098
-7.250 -0.6783 0.02004 0.01523 -0.0281 0.7332 0.0100
-7.000 -0.6566 0.01890 0.01389 -0.0272 0.7257 0.0102
-6.750 -0.6337 0.01794 0.01275 -0.0265 0.7189 0.0104
-6.500 -0.6099 0.01713 0.01178 -0.0258 0.7119 0.0105
-6.250 -0.5849 0.01656 0.01106 -0.0253 0.7054 0.0107
-6.000 -0.5642 0.01501 0.00931 -0.0242 0.6991 0.0111
-5.750 -0.5407 0.01414 0.00832 -0.0235 0.6932 0.0116
-5.500 -0.5146 0.01372 0.00786 -0.0231 0.6875 0.0121
-5.250 -0.4884 0.01332 0.00739 -0.0228 0.6815 0.0127
-5.000 -0.4622 0.01291 0.00688 -0.0224 0.6760 0.0133
-4.750 -0.4357 0.01250 0.00641 -0.0221 0.6708 0.0138
-4.500 -0.4088 0.01219 0.00602 -0.0218 0.6656 0.0142
-4.250 -0.3849 0.01134 0.00504 -0.0211 0.6607 0.0153
-4.000 -0.3581 0.01097 0.00464 -0.0208 0.6558 0.0162
-3.750 -0.3311 0.01067 0.00429 -0.0206 0.6508 0.0172
-3.500 -0.3038 0.01044 0.00398 -0.0204 0.6460 0.0182
-3.250 -0.2770 0.01004 0.00353 -0.0201 0.6417 0.0197
-3.000 -0.2499 0.00974 0.00319 -0.0198 0.6370 0.0217
-2.750 -0.2224 0.00954 0.00292 -0.0197 0.6324 0.0235
-2.500 -0.1950 0.00926 0.00263 -0.0195 0.6283 0.0277
-2.250 -0.1679 0.00896 0.00244 -0.0193 0.6238 0.0457
-2.000 -0.1401 0.00883 0.00229 -0.0192 0.6194 0.0570
-1.750 -0.1122 0.00871 0.00216 -0.0192 0.6153 0.0639
-1.250 -0.0563 0.00843 0.00193 -0.0191 0.6071 0.0820
-1.000 -0.0287 0.00829 0.00182 -0.0190 0.6029 0.1001
-0.750 -0.0012 0.00812 0.00173 -0.0190 0.5991 0.1266
-0.500 0.0263 0.00791 0.00165 -0.0189 0.5954 0.1602
-0.250 0.0538 0.00774 0.00157 -0.0189 0.5914 0.1960
0.000 0.0807 0.00756 0.00152 -0.0187 0.5873 0.2463
0.250 0.1079 0.00737 0.00148 -0.0186 0.5836 0.2957
0.500 0.1350 0.00717 0.00144 -0.0185 0.5797 0.3474
0.750 0.1618 0.00699 0.00141 -0.0184 0.5759 0.4049
1.000 0.1879 0.00680 0.00140 -0.0181 0.5719 0.4725
1.250 0.2131 0.00653 0.00139 -0.0176 0.5683 0.5584
1.500 0.2349 0.00612 0.00137 -0.0163 0.5645 0.6800
1.750 0.2810 0.00555 0.00159 -0.0199 0.5604 0.9487
2.000 0.3181 0.00573 0.00170 -0.0218 0.5560 0.9614
2.250 0.3558 0.00588 0.00184 -0.0237 0.5523 0.9707
2.500 0.4068 0.00605 0.00197 -0.0287 0.5477 0.9769
2.750 0.4475 0.00624 0.00211 -0.0313 0.5432 0.9836
3.000 0.4984 0.00633 0.00216 -0.0363 0.5384 0.9870
3.250 0.5521 0.00643 0.00225 -0.0419 0.5328 0.9940
3.500 0.6004 0.00640 0.00216 -0.0464 0.5268 0.9973
3.750 0.6425 0.00633 0.00209 -0.0496 0.5196 1.0000
4.000 0.6695 0.00640 0.00211 -0.0495 0.5120 1.0000
4.250 0.6966 0.00642 0.00214 -0.0494 0.5045 1.0000
4.500 0.7235 0.00649 0.00217 -0.0493 0.4913 1.0000
4.750 0.7503 0.00659 0.00221 -0.0493 0.4767 1.0000
5.000 0.7771 0.00670 0.00227 -0.0492 0.4607 1.0000
5.250 0.8039 0.00683 0.00234 -0.0491 0.4447 1.0000
5.500 0.8303 0.00704 0.00246 -0.0491 0.4216 1.0000
5.750 0.8562 0.00739 0.00263 -0.0491 0.3819 1.0000
6.000 0.8807 0.00808 0.00297 -0.0491 0.3134 1.0000
6.250 0.9028 0.00918 0.00358 -0.0491 0.2207 1.0000
6.500 0.9235 0.01027 0.00423 -0.0488 0.1394 1.0000
6.750 0.9412 0.01155 0.00505 -0.0480 0.0547 1.0000
7.000 0.9627 0.01211 0.00550 -0.0473 0.0338 1.0000
7.500 1.0052 0.01305 0.00633 -0.0457 0.0106 1.0000
7.750 1.0270 0.01338 0.00668 -0.0449 0.0097 1.0000
8.000 1.0482 0.01372 0.00705 -0.0440 0.0093 1.0000
8.250 1.0685 0.01410 0.00747 -0.0430 0.0089 1.0000
8.500 1.0879 0.01449 0.00789 -0.0419 0.0088 1.0000
8.750 1.1058 0.01494 0.00839 -0.0405 0.0085 1.0000
9.000 1.1219 0.01545 0.00894 -0.0388 0.0082 1.0000
9.250 1.1365 0.01598 0.00950 -0.0369 0.0081 1.0000
9.500 1.1490 0.01653 0.01011 -0.0347 0.0080 1.0000
9.750 1.1571 0.01721 0.01083 -0.0318 0.0078 1.0000
10.000 1.1507 0.01794 0.01163 -0.0266 0.0077 1.0000
10.250 1.1481 0.01874 0.01247 -0.0224 0.0076 1.0000
10.500 1.1495 0.01968 0.01346 -0.0191 0.0075 1.0000
10.750 1.1524 0.02074 0.01458 -0.0163 0.0074 1.0000
11.000 1.1575 0.02183 0.01572 -0.0141 0.0074 1.0000
11.250 1.1587 0.02331 0.01727 -0.0117 0.0072 1.0000
11.500 1.1630 0.02471 0.01873 -0.0099 0.0073 1.0000
11.750 1.1675 0.02621 0.02028 -0.0083 0.0072 1.0000
12.000 1.1678 0.02813 0.02228 -0.0067 0.0072 1.0000
12.250 1.1749 0.02958 0.02377 -0.0056 0.0073 1.0000
12.500 1.1664 0.03240 0.02667 -0.0038 0.0071 1.0000
12.750 1.1714 0.03414 0.02846 -0.0029 0.0071 1.0000
13.000 1.1765 0.03591 0.03028 -0.0020 0.0071 1.0000
13.250 1.1746 0.03829 0.03271 -0.0008 0.0071 1.0000
13.500 1.1793 0.04015 0.03463 0.0000 0.0071 1.0000
13.750 1.1798 0.04235 0.03687 0.0012 0.0070 1.0000
14.000 1.1857 0.04417 0.03873 0.0019 0.0071 1.0000
14.250 1.1928 0.04604 0.04069 0.0022 0.0069 1.0000
14.500 1.1970 0.04794 0.04263 0.0032 0.0070 1.0000
14.750 1.2059 0.04925 0.04392 0.0048 0.0071 1.0000
15.000 1.2131 0.05112 0.04584 0.0050 0.0071 1.0000
15.250 1.2221 0.05259 0.04734 0.0061 0.0071 1.0000
15.500 1.2303 0.05429 0.04911 0.0068 0.0071 1.0000
15.750 1.2358 0.05642 0.05131 0.0069 0.0072 1.0000
16.000 1.2426 0.05836 0.05333 0.0074 0.0072 1.0000
16.250 1.2525 0.05980 0.05481 0.0086 0.0072 1.0000
16.500 1.2503 0.06312 0.05828 0.0074 0.0074 1.0000
16.750 1.0768 0.06616 0.06183 0.0149 0.0073 1.0000
17.000 1.0784 0.06911 0.06485 0.0151 0.0073 1.0000
17.250 1.0786 0.07230 0.06812 0.0151 0.0073 1.0000
17.500 1.0723 0.07664 0.07261 0.0142 0.0074 1.0000
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