EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il) Reynolds number: 50,000 Max Cl/Cd: 25.81 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ste87151-il-50000-n5.txt Download as CSV file: xf-ste87151-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STE 871-514 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5291 0.10966 0.10297 -0.0380 1.0020 0.0507
-9.250 -0.5457 0.10400 0.09737 -0.0401 1.0020 0.0488
-8.750 -0.6148 0.09396 0.08728 -0.0407 1.0020 0.0453
-8.500 -0.6273 0.09087 0.08417 -0.0388 1.0020 0.0448
-8.250 -0.6398 0.08746 0.08072 -0.0371 1.0020 0.0443
-8.000 -0.6512 0.08392 0.07712 -0.0353 1.0020 0.0438
-7.750 -0.6608 0.08025 0.07335 -0.0336 1.0020 0.0432
-7.500 -0.6680 0.07646 0.06941 -0.0319 1.0020 0.0426
-7.250 -0.6724 0.07260 0.06534 -0.0304 1.0020 0.0420
-7.000 -0.6736 0.06870 0.06120 -0.0289 1.0020 0.0413
-6.750 -0.6713 0.06482 0.05700 -0.0275 1.0020 0.0407
-6.500 -0.6655 0.06096 0.05277 -0.0262 1.0020 0.0401
-6.250 -0.6559 0.05740 0.04881 -0.0251 1.0020 0.0398
-6.000 -0.6431 0.05431 0.04533 -0.0241 1.0020 0.0403
-5.750 -0.6277 0.05147 0.04209 -0.0233 1.0020 0.0413
-5.500 -0.6099 0.04882 0.03900 -0.0225 1.0020 0.0423
-5.250 -0.5901 0.04632 0.03602 -0.0217 1.0020 0.0432
-5.000 -0.5688 0.04402 0.03330 -0.0209 1.0020 0.0436
-4.750 -0.5463 0.04197 0.03085 -0.0201 1.0020 0.0441
-4.500 -0.5229 0.04018 0.02868 -0.0192 1.0019 0.0448
-4.250 -0.4916 0.03870 0.02686 -0.0196 0.9992 0.0459
-4.000 -0.4622 0.03746 0.02559 -0.0202 0.9968 0.0492
-3.750 -0.4332 0.03662 0.02460 -0.0202 0.9940 0.0533
-3.500 -0.4045 0.03597 0.02370 -0.0196 0.9913 0.0564
-3.250 -0.3771 0.03524 0.02297 -0.0195 0.9888 0.0615
-3.000 -0.3484 0.03476 0.02232 -0.0197 0.9862 0.0697
-2.750 -0.3233 0.03404 0.02157 -0.0197 0.9829 0.0809
-2.500 -0.2968 0.03324 0.02090 -0.0201 0.9798 0.1031
-2.250 -0.2824 0.03016 0.02087 -0.0187 0.9783 0.5279
-2.000 -0.2877 0.03227 0.02334 -0.0071 0.9731 0.8102
-1.750 -0.1745 0.03531 0.02576 -0.0125 0.9805 0.9706
-1.500 -0.1340 0.03550 0.02561 -0.0163 0.9773 0.9752
-1.250 -0.0991 0.03569 0.02553 -0.0189 0.9738 0.9796
-1.000 -0.0688 0.03579 0.02540 -0.0206 0.9691 0.9834
-0.750 -0.0342 0.03602 0.02543 -0.0232 0.9648 0.9866
-0.500 -0.0019 0.03629 0.02553 -0.0253 0.9603 0.9897
-0.250 0.0256 0.03644 0.02553 -0.0265 0.9545 0.9928
0.000 0.0596 0.03677 0.02573 -0.0290 0.9494 0.9953
0.250 0.0871 0.03697 0.02584 -0.0301 0.9429 0.9980
0.500 0.1111 0.03720 0.02598 -0.0305 0.9360 0.9980
0.750 0.1314 0.03738 0.02610 -0.0302 0.9285 0.9980
1.000 0.1543 0.03761 0.02629 -0.0303 0.9213 0.9980
1.250 0.1736 0.03780 0.02643 -0.0298 0.9135 0.9980
1.500 0.1965 0.03803 0.02664 -0.0298 0.9059 0.9980
1.750 0.2141 0.03819 0.02679 -0.0289 0.8973 0.9980
2.000 0.2391 0.03845 0.02705 -0.0293 0.8898 0.9980
2.250 0.2541 0.03855 0.02715 -0.0278 0.8799 0.9980
2.500 0.2837 0.03883 0.02745 -0.0289 0.8731 0.9980
2.750 0.2957 0.03884 0.02750 -0.0269 0.8618 0.9980
3.000 0.3148 0.03894 0.02764 -0.0260 0.8523 0.9980
3.250 0.3410 0.03906 0.02780 -0.0264 0.8439 0.9980
3.500 0.3548 0.03902 0.02782 -0.0246 0.8322 0.9980
3.750 0.3721 0.03898 0.02785 -0.0233 0.8210 0.9980
4.000 0.3939 0.03892 0.02787 -0.0227 0.8104 0.9980
4.250 0.4237 0.03880 0.02784 -0.0234 0.8011 0.9980
4.500 0.4434 0.03862 0.02775 -0.0224 0.7883 0.9980
4.750 0.4654 0.03840 0.02766 -0.0217 0.7753 0.9980
5.000 0.4893 0.03812 0.02750 -0.0212 0.7616 0.9980
5.250 0.5149 0.03777 0.02729 -0.0209 0.7473 0.9980
5.500 0.5423 0.03731 0.02697 -0.0206 0.7322 0.9980
5.750 0.5722 0.03662 0.02647 -0.0205 0.7162 0.9980
6.000 0.5966 0.03600 0.02602 -0.0195 0.6963 0.9980
6.250 0.6238 0.03510 0.02530 -0.0185 0.6746 0.9980
6.500 0.6537 0.03385 0.02425 -0.0175 0.6510 0.9980
6.750 0.6855 0.03249 0.02304 -0.0165 0.6215 0.9980
7.000 0.7098 0.03181 0.02246 -0.0149 0.5796 0.9980
7.250 0.7435 0.03067 0.02128 -0.0141 0.5224 0.9980
7.500 0.7758 0.03006 0.02027 -0.0132 0.4405 0.9980
7.750 0.7912 0.03079 0.02052 -0.0113 0.3631 0.9980
8.000 0.7998 0.03211 0.02143 -0.0092 0.2991 0.9980
8.250 0.8086 0.03360 0.02258 -0.0074 0.2503 0.9980
8.500 0.8196 0.03510 0.02382 -0.0061 0.2146 0.9980
8.750 0.8332 0.03653 0.02510 -0.0051 0.1884 0.9980
9.000 0.8497 0.03788 0.02632 -0.0044 0.1707 0.9980
9.250 0.8694 0.03912 0.02755 -0.0040 0.1562 0.9980
9.500 0.8920 0.04026 0.02874 -0.0039 0.1435 0.9980
9.750 0.9191 0.04133 0.02991 -0.0043 0.1332 0.9980
10.000 0.9522 0.04241 0.03098 -0.0052 0.1257 0.9980
10.250 0.9835 0.04362 0.03243 -0.0061 0.1180 0.9980
10.500 1.0149 0.04497 0.03374 -0.0071 0.1117 0.9980
10.750 1.0468 0.04664 0.03578 -0.0081 0.1066 0.9980
11.000 1.0768 0.04844 0.03781 -0.0090 0.1025 0.9980
11.250 1.1086 0.05040 0.03975 -0.0104 0.0985 0.9980
11.500 1.1199 0.05266 0.04250 -0.0092 0.0953 0.9980
11.750 1.1324 0.05508 0.04530 -0.0083 0.0924 0.9980
12.000 1.1439 0.05769 0.04825 -0.0074 0.0904 0.9980
12.250 1.1529 0.06029 0.05111 -0.0063 0.0885 0.9980
12.500 1.1637 0.06282 0.05379 -0.0056 0.0865 0.9980
12.750 1.1651 0.06580 0.05700 -0.0041 0.0848 0.9980
13.000 1.1485 0.06928 0.06090 -0.0012 0.0838 0.9980
13.250 1.1295 0.07311 0.06511 0.0012 0.0830 0.9980
13.500 1.1076 0.07738 0.06971 0.0031 0.0824 0.9980
13.750 1.0822 0.08227 0.07491 0.0042 0.0820 0.9980
14.000 1.0526 0.08802 0.08093 0.0043 0.0819 0.9980
14.250 1.0186 0.09493 0.08808 0.0029 0.0821 0.9980
14.500 0.9794 0.10370 0.09703 -0.0007 0.0826 0.9980
14.750 0.9357 0.11522 0.10865 -0.0071 0.0833 0.9980
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Polar data table (+)
Polar graphs
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