S8038 (13%) (s8038-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8038 (13%) (s8038-il) Reynolds number: 500,000 Max Cl/Cd: 71.63 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8038-il-500000.txt Download as CSV file: xf-s8038-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S8038 (13%)
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.8119 0.06873 0.06543 -0.0505 1.0000 0.0149
-13.500 -0.8324 0.06270 0.05925 -0.0538 1.0000 0.0149
-13.250 -0.8503 0.05752 0.05393 -0.0560 1.0000 0.0148
-13.000 -0.8716 0.05243 0.04865 -0.0575 1.0000 0.0147
-12.750 -0.8875 0.04866 0.04469 -0.0580 1.0000 0.0148
-12.500 -0.9013 0.04518 0.04103 -0.0575 1.0000 0.0148
-12.250 -0.9163 0.04167 0.03733 -0.0561 1.0000 0.0146
-12.000 -0.9250 0.03931 0.03479 -0.0541 1.0000 0.0146
-11.750 -0.9350 0.03736 0.03263 -0.0510 1.0000 0.0148
-11.500 -0.9421 0.03529 0.03040 -0.0474 1.0000 0.0147
-11.250 -0.9496 0.03395 0.02888 -0.0428 1.0000 0.0148
-11.000 -0.9493 0.03214 0.02690 -0.0394 1.0000 0.0148
-10.750 -0.9461 0.03138 0.02594 -0.0360 1.0000 0.0151
-10.500 -0.9424 0.02855 0.02290 -0.0333 1.0000 0.0154
-10.250 -0.9325 0.02680 0.02106 -0.0310 1.0000 0.0157
-10.000 -0.9207 0.02566 0.01986 -0.0288 1.0000 0.0160
-9.750 -0.9083 0.02451 0.01862 -0.0265 1.0000 0.0162
-9.500 -0.8953 0.02347 0.01750 -0.0242 1.0000 0.0164
-9.250 -0.8818 0.02257 0.01654 -0.0220 1.0000 0.0168
-9.000 -0.8681 0.02162 0.01552 -0.0197 1.0000 0.0170
-8.750 -0.8546 0.02072 0.01454 -0.0174 1.0000 0.0172
-8.500 -0.8408 0.01995 0.01372 -0.0150 1.0000 0.0176
-8.250 -0.8271 0.01924 0.01294 -0.0126 1.0000 0.0180
-8.000 -0.8141 0.01853 0.01217 -0.0101 1.0000 0.0183
-7.750 -0.8011 0.01791 0.01150 -0.0075 1.0000 0.0185
-7.500 -0.7786 0.01728 0.01081 -0.0069 0.9989 0.0190
-7.250 -0.7462 0.01610 0.00961 -0.0086 0.9956 0.0200
-7.000 -0.7115 0.01543 0.00892 -0.0105 0.9925 0.0211
-6.750 -0.6774 0.01481 0.00827 -0.0121 0.9884 0.0220
-6.500 -0.6414 0.01423 0.00764 -0.0141 0.9849 0.0231
-6.250 -0.6092 0.01347 0.00685 -0.0153 0.9799 0.0250
-6.000 -0.5752 0.01293 0.00630 -0.0167 0.9747 0.0277
-5.750 -0.5389 0.01229 0.00568 -0.0187 0.9712 0.0339
-5.500 -0.5122 0.01138 0.00500 -0.0188 0.9626 0.0692
-5.250 -0.4776 0.01066 0.00452 -0.0205 0.9584 0.1167
-5.000 -0.4491 0.01008 0.00413 -0.0209 0.9495 0.1588
-4.750 -0.4125 0.00947 0.00376 -0.0230 0.9446 0.2112
-4.500 -0.3795 0.00893 0.00343 -0.0244 0.9351 0.2674
-4.250 -0.3428 0.00831 0.00311 -0.0266 0.9274 0.3389
-4.000 -0.3093 0.00782 0.00285 -0.0280 0.9151 0.4049
-3.750 -0.2780 0.00744 0.00265 -0.0288 0.9004 0.4650
-3.500 -0.2494 0.00717 0.00253 -0.0289 0.8842 0.5200
-3.250 -0.2218 0.00707 0.00246 -0.0286 0.8675 0.5579
-3.000 -0.1948 0.00703 0.00239 -0.0282 0.8511 0.5807
-2.750 -0.1686 0.00702 0.00234 -0.0277 0.8352 0.6013
-2.500 -0.1427 0.00703 0.00230 -0.0270 0.8200 0.6185
-2.250 -0.1167 0.00703 0.00226 -0.0264 0.8056 0.6325
-2.000 -0.0906 0.00704 0.00222 -0.0258 0.7919 0.6452
-1.750 -0.0644 0.00707 0.00219 -0.0253 0.7789 0.6579
-1.500 -0.0384 0.00710 0.00217 -0.0247 0.7664 0.6705
-1.250 -0.0122 0.00711 0.00215 -0.0242 0.7545 0.6809
-1.000 0.0141 0.00713 0.00213 -0.0236 0.7419 0.6906
-0.750 0.0402 0.00715 0.00212 -0.0231 0.7295 0.7005
-0.500 0.0664 0.00716 0.00211 -0.0225 0.7171 0.7099
-0.250 0.0925 0.00721 0.00210 -0.0220 0.7052 0.7202
0.000 0.1186 0.00722 0.00211 -0.0215 0.6933 0.7293
0.250 0.1449 0.00724 0.00211 -0.0210 0.6813 0.7382
0.500 0.1711 0.00727 0.00212 -0.0205 0.6693 0.7474
0.750 0.1969 0.00729 0.00213 -0.0199 0.6559 0.7566
1.000 0.2226 0.00734 0.00213 -0.0193 0.6417 0.7666
1.250 0.2483 0.00735 0.00215 -0.0186 0.6279 0.7753
1.500 0.2740 0.00739 0.00217 -0.0181 0.6140 0.7851
1.750 0.2997 0.00742 0.00220 -0.0174 0.6001 0.7951
2.000 0.3253 0.00745 0.00224 -0.0168 0.5858 0.8053
2.250 0.3507 0.00749 0.00228 -0.0162 0.5714 0.8165
2.500 0.3760 0.00754 0.00233 -0.0155 0.5562 0.8280
2.750 0.4010 0.00758 0.00238 -0.0148 0.5398 0.8397
3.000 0.4256 0.00766 0.00244 -0.0140 0.5210 0.8523
3.250 0.4502 0.00773 0.00251 -0.0132 0.5003 0.8664
3.500 0.4750 0.00782 0.00259 -0.0124 0.4791 0.8819
3.750 0.5004 0.00794 0.00270 -0.0118 0.4568 0.8992
4.000 0.5288 0.00811 0.00283 -0.0119 0.4298 0.9175
4.250 0.5624 0.00836 0.00301 -0.0131 0.3988 0.9344
4.500 0.5998 0.00870 0.00323 -0.0153 0.3650 0.9472
4.750 0.6371 0.00908 0.00348 -0.0176 0.3275 0.9580
5.000 0.6737 0.00955 0.00376 -0.0197 0.2870 0.9671
5.250 0.7081 0.01002 0.00405 -0.0215 0.2496 0.9765
5.500 0.7422 0.01048 0.00437 -0.0231 0.2179 0.9857
5.750 0.7780 0.01094 0.00469 -0.0252 0.1905 0.9928
6.250 0.8424 0.01176 0.00531 -0.0279 0.1513 1.0000
6.500 0.8573 0.01208 0.00556 -0.0256 0.1400 1.0000
6.750 0.8745 0.01238 0.00583 -0.0236 0.1307 1.0000
7.000 0.8915 0.01274 0.00616 -0.0216 0.1223 1.0000
7.250 0.9094 0.01307 0.00646 -0.0198 0.1147 1.0000
7.500 0.9271 0.01344 0.00681 -0.0179 0.1080 1.0000
7.750 0.9456 0.01376 0.00713 -0.0162 0.1022 1.0000
8.000 0.9617 0.01423 0.00757 -0.0142 0.0965 1.0000
8.250 0.9813 0.01450 0.00788 -0.0127 0.0926 1.0000
8.500 0.9990 0.01488 0.00826 -0.0109 0.0888 1.0000
8.750 1.0127 0.01547 0.00882 -0.0085 0.0845 1.0000
9.000 1.0318 0.01577 0.00918 -0.0069 0.0822 1.0000
9.250 1.0500 0.01610 0.00956 -0.0053 0.0792 1.0000
9.500 1.0664 0.01653 0.00999 -0.0034 0.0761 1.0000
9.750 1.0773 0.01723 0.01068 -0.0006 0.0725 1.0000
10.000 1.0933 0.01759 0.01111 0.0014 0.0708 1.0000
10.250 1.1081 0.01797 0.01155 0.0036 0.0686 1.0000
10.500 1.1221 0.01839 0.01201 0.0058 0.0663 1.0000
10.750 1.1337 0.01895 0.01258 0.0083 0.0638 1.0000
11.000 1.1386 0.01994 0.01358 0.0116 0.0609 1.0000
11.250 1.1557 0.02029 0.01402 0.0131 0.0593 1.0000
11.500 1.1705 0.02079 0.01458 0.0148 0.0571 1.0000
11.750 1.1835 0.02141 0.01525 0.0167 0.0550 1.0000
12.000 1.1932 0.02224 0.01610 0.0187 0.0530 1.0000
12.250 1.1954 0.02363 0.01752 0.0215 0.0507 1.0000
12.500 1.2113 0.02415 0.01813 0.0226 0.0493 1.0000
12.750 1.2221 0.02506 0.01914 0.0241 0.0479 1.0000
13.000 1.2348 0.02585 0.01997 0.0253 0.0459 1.0000
13.250 1.2429 0.02702 0.02119 0.0267 0.0448 1.0000
13.500 1.2467 0.02857 0.02276 0.0282 0.0429 1.0000
13.750 1.2497 0.03030 0.02458 0.0295 0.0417 1.0000
14.000 1.2623 0.03131 0.02570 0.0301 0.0405 1.0000
14.250 1.2685 0.03291 0.02739 0.0310 0.0397 1.0000
14.500 1.2786 0.03420 0.02875 0.0314 0.0383 1.0000
14.750 1.2845 0.03592 0.03054 0.0318 0.0373 1.0000
15.000 1.2883 0.03792 0.03260 0.0321 0.0364 1.0000
15.250 1.2875 0.04040 0.03514 0.0324 0.0354 1.0000
15.750 1.2867 0.04558 0.04051 0.0325 0.0340 1.0000
16.000 1.2898 0.04795 0.04300 0.0321 0.0333 1.0000
16.250 1.2904 0.05065 0.04582 0.0317 0.0328 1.0000
16.500 1.2910 0.05345 0.04872 0.0310 0.0320 1.0000
16.750 1.2905 0.05646 0.05183 0.0301 0.0313 1.0000
17.000 1.2881 0.05980 0.05527 0.0291 0.0308 1.0000
17.250 1.2858 0.06331 0.05884 0.0277 0.0300 1.0000
17.500 1.2789 0.06742 0.06303 0.0262 0.0294 1.0000
17.750 1.2701 0.07189 0.06756 0.0244 0.0287 1.0000
18.000 1.2599 0.07656 0.07233 0.0227 0.0284 1.0000
18.250 1.2504 0.08136 0.07724 0.0206 0.0279 1.0000
18.500 1.2424 0.08619 0.08221 0.0183 0.0276 1.0000
18.750 1.2335 0.09126 0.08741 0.0159 0.0273 1.0000
19.000 1.2234 0.09670 0.09298 0.0131 0.0267 1.0000
19.250 1.2114 0.10238 0.09878 0.0102 0.0264 1.0000
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Polar data table (+)
Polar graphs
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