SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7090 (10%) (sd7090-il) Reynolds number: 500,000 Max Cl/Cd: 78.28 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7090-il-500000-n5.txt Download as CSV file: xf-sd7090-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7444 0.08467 0.08205 -0.0299 1.0000 0.0101
-13.000 -0.8387 0.06107 0.05822 -0.0449 1.0000 0.0095
-12.750 -0.8777 0.04755 0.04445 -0.0571 1.0000 0.0094
-12.500 -0.8998 0.04099 0.03766 -0.0625 1.0000 0.0094
-12.250 -0.9189 0.03727 0.03376 -0.0628 1.0000 0.0094
-12.000 -0.9314 0.03520 0.03152 -0.0599 1.0000 0.0095
-11.750 -0.9386 0.03300 0.02912 -0.0571 1.0000 0.0096
-11.500 -0.9349 0.03137 0.02729 -0.0550 1.0000 0.0098
-11.250 -0.9328 0.02943 0.02516 -0.0527 1.0000 0.0100
-11.000 -0.9256 0.02789 0.02348 -0.0506 1.0000 0.0102
-10.750 -0.9141 0.02671 0.02220 -0.0489 1.0000 0.0104
-10.500 -0.8997 0.02581 0.02122 -0.0473 1.0000 0.0107
-10.250 -0.8846 0.02492 0.02022 -0.0457 1.0000 0.0109
-10.000 -0.8699 0.02387 0.01903 -0.0441 1.0000 0.0112
-9.750 -0.8541 0.02289 0.01792 -0.0425 1.0000 0.0115
-9.500 -0.8380 0.02187 0.01676 -0.0409 1.0000 0.0118
-9.250 -0.8210 0.02092 0.01566 -0.0393 1.0000 0.0122
-9.000 -0.8034 0.02003 0.01462 -0.0378 1.0000 0.0125
-8.750 -0.7850 0.01922 0.01367 -0.0364 1.0000 0.0128
-8.500 -0.7652 0.01864 0.01297 -0.0351 1.0000 0.0131
-8.250 -0.7413 0.01752 0.01175 -0.0350 0.9990 0.0137
-8.000 -0.7104 0.01675 0.01091 -0.0361 0.9969 0.0142
-7.750 -0.6785 0.01610 0.01019 -0.0373 0.9948 0.0147
-7.500 -0.6474 0.01546 0.00947 -0.0383 0.9926 0.0152
-7.250 -0.6170 0.01484 0.00876 -0.0391 0.9897 0.0157
-7.000 -0.5852 0.01428 0.00812 -0.0401 0.9870 0.0163
-6.750 -0.5518 0.01382 0.00759 -0.0414 0.9847 0.0170
-6.500 -0.5208 0.01317 0.00688 -0.0423 0.9817 0.0177
-6.250 -0.4918 0.01263 0.00630 -0.0427 0.9771 0.0185
-6.000 -0.4595 0.01219 0.00583 -0.0437 0.9735 0.0194
-5.500 -0.3989 0.01142 0.00496 -0.0448 0.9632 0.0214
-5.000 -0.3383 0.01067 0.00419 -0.0458 0.9503 0.0256
-4.750 -0.3046 0.01032 0.00383 -0.0470 0.9443 0.0296
-4.500 -0.2730 0.01000 0.00353 -0.0477 0.9351 0.0365
-4.250 -0.2378 0.00970 0.00324 -0.0492 0.9263 0.0457
-4.000 -0.2022 0.00942 0.00297 -0.0508 0.9147 0.0547
-3.750 -0.1681 0.00917 0.00271 -0.0520 0.8991 0.0649
-3.500 -0.1370 0.00896 0.00249 -0.0526 0.8795 0.0763
-3.250 -0.1083 0.00879 0.00230 -0.0526 0.8583 0.0901
-3.000 -0.0813 0.00863 0.00212 -0.0523 0.8372 0.1106
-2.750 -0.0553 0.00844 0.00198 -0.0518 0.8163 0.1408
-2.500 -0.0296 0.00828 0.00185 -0.0513 0.7961 0.1735
-2.250 -0.0039 0.00813 0.00173 -0.0508 0.7767 0.2099
-2.000 0.0216 0.00797 0.00164 -0.0503 0.7572 0.2495
-1.750 0.0473 0.00785 0.00155 -0.0497 0.7381 0.2881
-1.500 0.0728 0.00773 0.00148 -0.0492 0.7195 0.3293
-1.250 0.0982 0.00758 0.00142 -0.0487 0.7007 0.3803
-1.000 0.1232 0.00739 0.00138 -0.0481 0.6823 0.4459
-0.750 0.1477 0.00718 0.00135 -0.0474 0.6636 0.5227
-0.500 0.1721 0.00702 0.00135 -0.0466 0.6446 0.5937
-0.250 0.1967 0.00691 0.00136 -0.0457 0.6254 0.6550
0.000 0.2214 0.00685 0.00138 -0.0449 0.6052 0.7056
0.250 0.2462 0.00684 0.00141 -0.0441 0.5848 0.7464
0.500 0.2711 0.00684 0.00144 -0.0432 0.5643 0.7818
0.750 0.2959 0.00687 0.00149 -0.0424 0.5438 0.8144
1.000 0.3205 0.00691 0.00154 -0.0414 0.5230 0.8468
1.250 0.3455 0.00696 0.00160 -0.0406 0.5021 0.8797
1.500 0.3724 0.00706 0.00167 -0.0401 0.4810 0.9111
1.750 0.4045 0.00720 0.00175 -0.0408 0.4596 0.9378
2.000 0.4395 0.00737 0.00183 -0.0423 0.4361 0.9580
2.250 0.4750 0.00755 0.00191 -0.0439 0.4135 0.9733
2.500 0.5101 0.00774 0.00201 -0.0455 0.3908 0.9845
2.750 0.5462 0.00794 0.00210 -0.0473 0.3685 0.9922
3.000 0.5821 0.00814 0.00220 -0.0492 0.3468 0.9988
3.250 0.6076 0.00834 0.00231 -0.0487 0.3281 1.0000
3.500 0.6305 0.00853 0.00243 -0.0477 0.3103 1.0000
3.750 0.6535 0.00873 0.00256 -0.0467 0.2926 1.0000
4.000 0.6766 0.00895 0.00271 -0.0458 0.2758 1.0000
4.250 0.6997 0.00918 0.00286 -0.0448 0.2588 1.0000
4.500 0.7229 0.00942 0.00303 -0.0439 0.2421 1.0000
5.000 0.7699 0.00992 0.00341 -0.0422 0.2114 1.0000
5.250 0.7935 0.01019 0.00362 -0.0414 0.1963 1.0000
5.500 0.8172 0.01047 0.00384 -0.0406 0.1814 1.0000
5.750 0.8409 0.01076 0.00409 -0.0398 0.1674 1.0000
6.000 0.8647 0.01105 0.00434 -0.0391 0.1549 1.0000
6.250 0.8885 0.01135 0.00460 -0.0384 0.1424 1.0000
6.500 0.9121 0.01167 0.00488 -0.0376 0.1299 1.0000
6.750 0.9357 0.01199 0.00518 -0.0369 0.1190 1.0000
7.000 0.9592 0.01234 0.00549 -0.0362 0.1089 1.0000
7.250 0.9823 0.01271 0.00582 -0.0354 0.0986 1.0000
7.500 1.0056 0.01306 0.00616 -0.0346 0.0897 1.0000
7.750 1.0288 0.01343 0.00653 -0.0339 0.0821 1.0000
8.000 1.0513 0.01385 0.00692 -0.0330 0.0739 1.0000
8.250 1.0740 0.01423 0.00732 -0.0322 0.0668 1.0000
8.500 1.0963 0.01467 0.00774 -0.0314 0.0604 1.0000
8.750 1.1181 0.01512 0.00819 -0.0305 0.0542 1.0000
9.000 1.1399 0.01556 0.00866 -0.0296 0.0495 1.0000
9.250 1.1613 0.01604 0.00915 -0.0286 0.0450 1.0000
9.500 1.1820 0.01655 0.00968 -0.0276 0.0411 1.0000
9.750 1.2028 0.01703 0.01020 -0.0265 0.0376 1.0000
10.000 1.2222 0.01762 0.01080 -0.0253 0.0342 1.0000
10.250 1.2421 0.01813 0.01138 -0.0242 0.0317 1.0000
10.500 1.2610 0.01870 0.01197 -0.0230 0.0290 1.0000
10.750 1.2781 0.01937 0.01266 -0.0215 0.0261 1.0000
11.000 1.2964 0.01991 0.01327 -0.0202 0.0244 1.0000
11.250 1.3130 0.02054 0.01395 -0.0187 0.0226 1.0000
11.500 1.3268 0.02126 0.01471 -0.0167 0.0210 1.0000
11.750 1.3395 0.02193 0.01545 -0.0146 0.0198 1.0000
12.000 1.3521 0.02259 0.01619 -0.0125 0.0185 1.0000
12.250 1.3632 0.02335 0.01701 -0.0103 0.0173 1.0000
12.500 1.3724 0.02425 0.01796 -0.0081 0.0161 1.0000
12.750 1.3817 0.02516 0.01895 -0.0060 0.0153 1.0000
13.000 1.3909 0.02610 0.01999 -0.0040 0.0144 1.0000
13.250 1.3984 0.02719 0.02116 -0.0021 0.0137 1.0000
13.500 1.4045 0.02843 0.02249 -0.0003 0.0128 1.0000
13.750 1.4082 0.02993 0.02407 0.0014 0.0122 1.0000
14.000 1.4126 0.03147 0.02572 0.0028 0.0115 1.0000
14.250 1.4157 0.03323 0.02759 0.0040 0.0110 1.0000
14.500 1.4178 0.03520 0.02966 0.0048 0.0104 1.0000
14.750 1.4178 0.03751 0.03207 0.0054 0.0098 1.0000
15.000 1.4161 0.04018 0.03485 0.0056 0.0095 1.0000
15.250 1.4119 0.04331 0.03808 0.0054 0.0090 1.0000
15.500 1.4092 0.04647 0.04138 0.0049 0.0087 1.0000
15.750 1.4026 0.05032 0.04536 0.0038 0.0085 1.0000
16.000 1.3951 0.05450 0.04969 0.0024 0.0081 1.0000
16.250 1.3851 0.05926 0.05458 0.0005 0.0079 1.0000
16.500 1.3733 0.06449 0.05996 -0.0018 0.0077 1.0000
16.750 1.3595 0.07027 0.06588 -0.0045 0.0075 1.0000
17.000 1.3431 0.07673 0.07248 -0.0078 0.0074 1.0000
17.250 1.3255 0.08365 0.07955 -0.0113 0.0074 1.0000
17.500 1.3053 0.09121 0.08726 -0.0153 0.0075 1.0000
17.750 1.2842 0.09923 0.09542 -0.0196 0.0073 1.0000
18.000 1.2622 0.10761 0.10395 -0.0242 0.0074 1.0000
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Polar data table (+)
Polar graphs
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