SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7090 (10%) (sd7090-il) Reynolds number: 1,000,000 Max Cl/Cd: 99 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7090-il-1000000.txt Download as CSV file: xf-sd7090-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SD7090 (10%)
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7932 0.03879 0.03649 -0.0543 1.0000 0.0098
-12.750 -0.8768 0.04652 0.04407 -0.0579 1.0000 0.0094
-12.500 -0.8941 0.04057 0.03795 -0.0631 1.0000 0.0094
-12.250 -0.9119 0.03683 0.03404 -0.0639 1.0000 0.0094
-11.750 -0.9484 0.03166 0.02849 -0.0567 1.0000 0.0095
-11.500 -0.9665 0.02791 0.02441 -0.0527 1.0000 0.0098
-11.250 -0.9620 0.02614 0.02248 -0.0503 1.0000 0.0100
-11.000 -0.9512 0.02495 0.02120 -0.0483 1.0000 0.0102
-10.750 -0.9372 0.02402 0.02019 -0.0466 1.0000 0.0104
-10.500 -0.9218 0.02320 0.01929 -0.0450 1.0000 0.0106
-10.250 -0.9053 0.02246 0.01847 -0.0434 1.0000 0.0109
-10.000 -0.8901 0.02144 0.01733 -0.0417 1.0000 0.0111
-9.750 -0.8734 0.02057 0.01635 -0.0401 1.0000 0.0114
-9.500 -0.8558 0.01981 0.01547 -0.0386 1.0000 0.0117
-9.250 -0.8375 0.01909 0.01465 -0.0371 1.0000 0.0120
-9.000 -0.8177 0.01862 0.01410 -0.0357 1.0000 0.0123
-8.750 -0.7974 0.01822 0.01361 -0.0344 1.0000 0.0125
-8.500 -0.7858 0.01613 0.01132 -0.0322 1.0000 0.0131
-8.250 -0.7627 0.01541 0.01055 -0.0316 0.9996 0.0135
-8.000 -0.7297 0.01489 0.00997 -0.0330 0.9982 0.0140
-7.750 -0.6965 0.01428 0.00930 -0.0344 0.9965 0.0146
-7.500 -0.6625 0.01377 0.00872 -0.0359 0.9951 0.0152
-7.250 -0.6283 0.01323 0.00812 -0.0374 0.9938 0.0156
-7.000 -0.5960 0.01291 0.00775 -0.0384 0.9915 0.0160
-6.750 -0.5653 0.01182 0.00655 -0.0394 0.9889 0.0170
-6.500 -0.5315 0.01130 0.00601 -0.0408 0.9869 0.0179
-6.250 -0.4963 0.01089 0.00556 -0.0424 0.9853 0.0187
-6.000 -0.4603 0.01051 0.00514 -0.0442 0.9840 0.0196
-5.750 -0.4290 0.01019 0.00480 -0.0449 0.9806 0.0203
-5.500 -0.3975 0.00963 0.00420 -0.0457 0.9769 0.0219
-5.250 -0.3627 0.00927 0.00382 -0.0472 0.9744 0.0235
-5.000 -0.3262 0.00896 0.00350 -0.0489 0.9724 0.0254
-4.750 -0.2923 0.00857 0.00313 -0.0502 0.9693 0.0297
-4.500 -0.2636 0.00823 0.00284 -0.0502 0.9622 0.0388
-4.250 -0.2295 0.00793 0.00259 -0.0515 0.9577 0.0511
-4.000 -0.2010 0.00768 0.00238 -0.0515 0.9470 0.0610
-3.750 -0.1684 0.00743 0.00216 -0.0524 0.9365 0.0716
-3.500 -0.1357 0.00721 0.00195 -0.0533 0.9227 0.0842
-3.250 -0.1053 0.00702 0.00177 -0.0537 0.9039 0.1013
-3.000 -0.0776 0.00683 0.00161 -0.0535 0.8821 0.1279
-2.750 -0.0516 0.00666 0.00148 -0.0530 0.8596 0.1619
-2.500 -0.0261 0.00649 0.00137 -0.0524 0.8382 0.2051
-2.250 -0.0009 0.00628 0.00127 -0.0518 0.8168 0.2579
-2.000 0.0244 0.00611 0.00119 -0.0513 0.7966 0.3113
-1.750 0.0497 0.00595 0.00113 -0.0507 0.7776 0.3660
-1.500 0.0753 0.00579 0.00107 -0.0502 0.7587 0.4207
-1.250 0.1008 0.00564 0.00103 -0.0496 0.7400 0.4794
-1.000 0.1260 0.00548 0.00101 -0.0490 0.7216 0.5455
-0.750 0.1511 0.00534 0.00100 -0.0483 0.7029 0.6102
-0.500 0.1764 0.00525 0.00100 -0.0477 0.6843 0.6663
-0.250 0.2015 0.00516 0.00102 -0.0469 0.6650 0.7215
0.000 0.2269 0.00513 0.00104 -0.0462 0.6451 0.7625
0.250 0.2521 0.00513 0.00106 -0.0454 0.6251 0.7981
0.500 0.2775 0.00513 0.00109 -0.0447 0.6049 0.8313
0.750 0.3025 0.00515 0.00112 -0.0438 0.5836 0.8630
1.000 0.3272 0.00519 0.00117 -0.0429 0.5632 0.8945
1.250 0.3526 0.00525 0.00123 -0.0421 0.5419 0.9248
1.750 0.4144 0.00551 0.00136 -0.0430 0.4970 0.9682
2.000 0.4494 0.00569 0.00142 -0.0445 0.4736 0.9790
2.250 0.4856 0.00585 0.00149 -0.0463 0.4497 0.9857
2.500 0.5229 0.00603 0.00156 -0.0484 0.4254 0.9906
2.750 0.5600 0.00621 0.00164 -0.0504 0.4009 0.9953
3.000 0.5989 0.00639 0.00171 -0.0529 0.3768 0.9990
3.250 0.6267 0.00656 0.00180 -0.0530 0.3557 1.0000
3.500 0.6491 0.00674 0.00189 -0.0518 0.3372 1.0000
3.750 0.6718 0.00691 0.00199 -0.0508 0.3179 1.0000
4.000 0.6948 0.00710 0.00211 -0.0497 0.3006 1.0000
4.250 0.7176 0.00731 0.00223 -0.0487 0.2813 1.0000
4.750 0.7640 0.00774 0.00252 -0.0468 0.2464 1.0000
5.000 0.7874 0.00796 0.00268 -0.0459 0.2298 1.0000
5.250 0.8108 0.00819 0.00284 -0.0449 0.2132 1.0000
5.500 0.8343 0.00844 0.00302 -0.0441 0.1971 1.0000
5.750 0.8579 0.00870 0.00322 -0.0432 0.1813 1.0000
6.000 0.8816 0.00897 0.00342 -0.0425 0.1665 1.0000
6.250 0.9055 0.00924 0.00364 -0.0417 0.1528 1.0000
6.500 0.9296 0.00951 0.00386 -0.0410 0.1406 1.0000
6.750 0.9535 0.00980 0.00411 -0.0403 0.1282 1.0000
7.000 0.9774 0.01010 0.00436 -0.0396 0.1172 1.0000
7.250 1.0011 0.01042 0.00464 -0.0388 0.1060 1.0000
7.500 1.0247 0.01076 0.00493 -0.0381 0.0955 1.0000
7.750 1.0486 0.01107 0.00521 -0.0374 0.0869 1.0000
8.000 1.0721 0.01140 0.00553 -0.0367 0.0783 1.0000
8.250 1.0950 0.01180 0.00588 -0.0359 0.0692 1.0000
8.500 1.1183 0.01215 0.00621 -0.0352 0.0628 1.0000
8.750 1.1412 0.01253 0.00658 -0.0344 0.0560 1.0000
9.000 1.1634 0.01298 0.00699 -0.0335 0.0496 1.0000
9.250 1.1861 0.01335 0.00738 -0.0327 0.0448 1.0000
9.500 1.2072 0.01387 0.00786 -0.0317 0.0390 1.0000
9.750 1.2299 0.01422 0.00825 -0.0309 0.0361 1.0000
10.000 1.2506 0.01475 0.00875 -0.0298 0.0322 1.0000
10.250 1.2720 0.01518 0.00922 -0.0288 0.0298 1.0000
10.500 1.2931 0.01562 0.00969 -0.0279 0.0276 1.0000
10.750 1.3117 0.01626 0.01033 -0.0265 0.0247 1.0000
11.000 1.3325 0.01667 0.01079 -0.0255 0.0233 1.0000
11.250 1.3522 0.01715 0.01130 -0.0244 0.0217 1.0000
11.500 1.3693 0.01781 0.01197 -0.0228 0.0198 1.0000
11.750 1.3866 0.01840 0.01262 -0.0213 0.0186 1.0000
12.000 1.4047 0.01889 0.01316 -0.0200 0.0175 1.0000
12.250 1.4194 0.01949 0.01380 -0.0181 0.0162 1.0000
12.500 1.4274 0.02036 0.01471 -0.0152 0.0148 1.0000
12.750 1.4412 0.02088 0.01529 -0.0132 0.0141 1.0000
13.000 1.4532 0.02152 0.01598 -0.0110 0.0132 1.0000
13.250 1.4620 0.02236 0.01686 -0.0086 0.0121 1.0000
13.500 1.4670 0.02346 0.01802 -0.0059 0.0112 1.0000
13.750 1.4777 0.02424 0.01888 -0.0040 0.0107 1.0000
14.000 1.4855 0.02523 0.01994 -0.0020 0.0101 1.0000
14.250 1.4894 0.02655 0.02133 0.0001 0.0094 1.0000
14.500 1.4896 0.02821 0.02307 0.0022 0.0088 1.0000
14.750 1.4903 0.02998 0.02494 0.0039 0.0085 1.0000
15.000 1.4944 0.03161 0.02666 0.0051 0.0081 1.0000
15.250 1.4966 0.03351 0.02866 0.0060 0.0079 1.0000
15.500 1.4962 0.03581 0.03105 0.0067 0.0077 1.0000
15.750 1.4947 0.03839 0.03373 0.0069 0.0072 1.0000
16.000 1.4907 0.04144 0.03687 0.0068 0.0070 1.0000
16.250 1.4835 0.04509 0.04064 0.0062 0.0069 1.0000
16.500 1.4702 0.04976 0.04544 0.0049 0.0066 1.0000
16.750 1.4568 0.05478 0.05060 0.0031 0.0066 1.0000
17.000 1.4411 0.06042 0.05637 0.0007 0.0065 1.0000
17.250 1.4160 0.06789 0.06401 -0.0029 0.0064 1.0000
17.500 1.4064 0.07311 0.06935 -0.0054 0.0065 1.0000
17.750 1.3775 0.08186 0.07826 -0.0099 0.0064 1.0000
18.000 1.3525 0.09025 0.08680 -0.0144 0.0064 1.0000
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Polar data table (+)
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