SA7038 (sa7038-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 50,000 Max Cl/Cd: 34.64 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7038-il-50000.txt Download as CSV file: xf-sa7038-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SA7038
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3549 0.10394 0.09729 -0.0243 1.0000 0.2129
-8.000 -0.3471 0.10037 0.09378 -0.0234 1.0000 0.2206
-7.750 -0.3643 0.09992 0.09350 -0.0234 1.0000 0.2287
-7.500 -0.3524 0.09612 0.08973 -0.0218 1.0000 0.2412
-7.250 -0.3481 0.09307 0.08677 -0.0202 1.0000 0.2517
-7.000 -0.3783 0.09347 0.08740 -0.0185 1.0000 0.2579
-6.750 -0.3714 0.09024 0.08422 -0.0163 1.0000 0.2714
-6.500 -0.3653 0.08711 0.08114 -0.0141 1.0000 0.2830
-6.250 -0.3703 0.08487 0.07901 -0.0117 1.0000 0.2936
-6.000 -0.3818 0.08314 0.07742 -0.0099 1.0000 0.3050
-5.500 -0.3901 0.07870 0.07317 -0.0051 1.0000 0.3342
-5.250 -0.3912 0.07639 0.07094 -0.0024 1.0000 0.3498
-5.000 -0.3916 0.07406 0.06869 0.0006 1.0000 0.3682
-4.000 -0.3169 0.04670 0.03984 -0.0435 1.0000 0.1468
-3.750 -0.2854 0.04134 0.03373 -0.0468 1.0000 0.1246
-3.500 -0.2537 0.03721 0.02863 -0.0487 1.0000 0.1136
-3.250 -0.2283 0.03441 0.02546 -0.0490 1.0000 0.1120
-3.000 -0.2009 0.03221 0.02265 -0.0492 1.0000 0.1138
-2.750 -0.1762 0.03018 0.02049 -0.0491 1.0000 0.1190
-2.500 -0.1502 0.02854 0.01851 -0.0488 1.0000 0.1229
-2.250 -0.1242 0.02704 0.01662 -0.0481 1.0000 0.1300
-2.000 -0.1011 0.02585 0.01546 -0.0474 1.0000 0.1486
-1.750 -0.0765 0.02463 0.01432 -0.0466 1.0000 0.1890
-1.500 -0.0463 0.02135 0.01314 -0.0464 1.0000 0.4999
-1.250 -0.0377 0.01969 0.01253 -0.0408 1.0000 1.0000
-1.000 -0.0154 0.02010 0.01231 -0.0408 1.0000 1.0000
-0.750 0.0055 0.02056 0.01233 -0.0407 1.0000 1.0000
-0.500 0.0258 0.02107 0.01249 -0.0406 1.0000 1.0000
-0.250 0.0455 0.02164 0.01276 -0.0406 1.0000 1.0000
0.000 0.0646 0.02227 0.01310 -0.0405 1.0000 1.0000
0.250 0.0833 0.02295 0.01356 -0.0405 1.0000 1.0000
0.500 0.1090 0.02385 0.01424 -0.0419 0.9965 1.0000
0.750 0.1621 0.02526 0.01538 -0.0481 0.9794 1.0000
1.000 0.2117 0.02650 0.01640 -0.0535 0.9616 1.0000
1.250 0.2619 0.02767 0.01740 -0.0588 0.9441 1.0000
1.500 0.3051 0.02861 0.01822 -0.0626 0.9255 1.0000
1.750 0.3464 0.02944 0.01897 -0.0658 0.9064 1.0000
2.000 0.3916 0.03020 0.01967 -0.0694 0.8883 1.0000
2.250 0.4345 0.03085 0.02028 -0.0724 0.8700 1.0000
2.500 0.4691 0.03142 0.02086 -0.0740 0.8502 1.0000
2.750 0.5125 0.03182 0.02128 -0.0765 0.8320 1.0000
3.000 0.5618 0.03195 0.02146 -0.0795 0.8148 1.0000
3.250 0.5893 0.03241 0.02196 -0.0795 0.7937 1.0000
3.500 0.6353 0.03228 0.02192 -0.0814 0.7756 1.0000
3.750 0.6834 0.03179 0.02157 -0.0830 0.7588 1.0000
4.000 0.7130 0.03192 0.02178 -0.0825 0.7381 1.0000
4.250 0.7526 0.03146 0.02143 -0.0826 0.7195 1.0000
4.500 0.7975 0.03057 0.02070 -0.0828 0.7019 1.0000
4.750 0.8246 0.03064 0.02087 -0.0815 0.6796 1.0000
5.000 0.8647 0.02985 0.02017 -0.0809 0.6598 1.0000
5.250 0.8922 0.02987 0.02033 -0.0794 0.6365 1.0000
5.500 0.9298 0.02921 0.01970 -0.0785 0.6147 1.0000
5.750 0.9547 0.02945 0.02002 -0.0768 0.5894 1.0000
6.000 0.9804 0.02970 0.02032 -0.0752 0.5641 1.0000
6.250 1.0075 0.02991 0.02060 -0.0737 0.5390 1.0000
6.500 1.0354 0.03009 0.02076 -0.0722 0.5135 1.0000
6.750 1.0595 0.03059 0.02129 -0.0706 0.4874 1.0000
7.000 1.0809 0.03134 0.02210 -0.0689 0.4610 1.0000
7.250 1.1025 0.03211 0.02295 -0.0672 0.4348 1.0000
7.500 1.1248 0.03295 0.02380 -0.0656 0.4096 1.0000
7.750 1.1482 0.03373 0.02454 -0.0641 0.3843 1.0000
8.000 1.1683 0.03479 0.02565 -0.0624 0.3593 1.0000
8.250 1.1856 0.03613 0.02711 -0.0606 0.3352 1.0000
8.500 1.2055 0.03730 0.02832 -0.0589 0.3112 1.0000
8.750 1.2263 0.03845 0.02940 -0.0574 0.2872 1.0000
9.000 1.2384 0.04017 0.03133 -0.0551 0.2650 1.0000
9.250 1.2580 0.04158 0.03265 -0.0536 0.2427 1.0000
9.500 1.2680 0.04366 0.03498 -0.0513 0.2232 1.0000
9.750 1.2875 0.04538 0.03659 -0.0499 0.2031 1.0000
10.000 1.2967 0.04778 0.03916 -0.0477 0.1867 1.0000
10.250 1.3065 0.05060 0.04224 -0.0456 0.1730 1.0000
10.500 1.3147 0.05316 0.04495 -0.0435 0.1597 1.0000
10.750 1.3104 0.05662 0.04886 -0.0406 0.1515 1.0000
11.000 1.3097 0.06046 0.05295 -0.0384 0.1447 1.0000
11.250 1.2910 0.06474 0.05767 -0.0353 0.1417 1.0000
11.500 1.2968 0.06752 0.06047 -0.0336 0.1321 1.0000
11.750 1.2706 0.07186 0.06511 -0.0307 0.1317 1.0000
12.000 1.2428 0.07673 0.07022 -0.0289 0.1320 1.0000
12.250 1.2152 0.08240 0.07606 -0.0287 0.1327 1.0000
12.500 1.1877 0.08889 0.08268 -0.0299 0.1336 1.0000
12.750 0.9578 0.14088 0.13390 -0.0690 0.2039 1.0000
13.000 0.9653 0.14650 0.13961 -0.0698 0.2023 1.0000
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Polar data table (+)
Polar graphs
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