EPPLER STE 871-514 AIRFOIL (ste87151-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER STE 871-514 AIRFOIL (ste87151-il) Reynolds number: 500,000 Max Cl/Cd: 81.81 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ste87151-il-500000.txt Download as CSV file: xf-ste87151-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2440 0.08891 0.08625 -0.1152 0.9493 0.0178
-11.000 -0.2436 0.08448 0.08183 -0.1180 0.9484 0.0182
-10.750 -0.2461 0.07910 0.07645 -0.1218 0.9475 0.0186
-10.500 -0.2555 0.07114 0.06851 -0.1291 0.9463 0.0187
-10.250 -0.2733 0.06399 0.06127 -0.1349 0.9450 0.0186
-10.000 -0.2897 0.05898 0.05616 -0.1377 0.9434 0.0188
-9.750 -0.3072 0.05513 0.05218 -0.1381 0.9412 0.0191
-9.250 -0.3656 0.04730 0.04375 -0.1303 0.9349 0.0203
-9.000 -0.3598 0.04588 0.04232 -0.1288 0.9340 0.0205
-8.750 -0.4424 0.04877 0.04512 -0.1071 0.9255 0.0202
-8.500 -0.4416 0.04733 0.04369 -0.1041 0.9237 0.0204
-8.250 -0.4374 0.04600 0.04233 -0.1018 0.9224 0.0206
-8.000 -0.4258 0.04426 0.04050 -0.1010 0.9214 0.0212
-7.750 -0.4459 0.03624 0.03276 -0.0853 0.9121 0.0212
-7.500 -0.4430 0.03385 0.03019 -0.0826 0.9100 0.0222
-7.250 -0.4396 0.02967 0.02557 -0.0802 0.9083 0.0239
-7.000 -0.4187 0.02768 0.02348 -0.0806 0.9074 0.0246
-6.750 -0.3982 0.02429 0.01959 -0.0805 0.9064 0.0273
-6.500 -0.3690 0.02250 0.01778 -0.0820 0.9059 0.0283
-6.250 -0.3418 0.02042 0.01540 -0.0829 0.9051 0.0315
-5.750 -0.3473 0.02541 0.01895 -0.0734 0.8996 0.0169
-5.500 -0.3228 0.02387 0.01739 -0.0729 0.8980 0.0165
-5.250 -0.2962 0.02279 0.01622 -0.0727 0.8966 0.0163
-5.000 -0.2681 0.02192 0.01526 -0.0729 0.8954 0.0165
-4.750 -0.2394 0.02120 0.01445 -0.0732 0.8944 0.0170
-4.500 -0.2097 0.02047 0.01376 -0.0740 0.8935 0.0181
-4.250 -0.1771 0.01996 0.01323 -0.0752 0.8926 0.0194
-4.000 -0.1436 0.01937 0.01264 -0.0767 0.8918 0.0209
-3.750 -0.1094 0.01902 0.01228 -0.0783 0.8912 0.0231
-3.500 -0.1038 0.01903 0.01231 -0.0745 0.8856 0.0251
-3.250 -0.0815 0.01878 0.01206 -0.0738 0.8823 0.0284
-3.000 -0.0523 0.01846 0.01177 -0.0745 0.8806 0.0352
-2.750 -0.0174 0.01741 0.01138 -0.0770 0.8797 0.1807
-2.500 0.0273 0.01552 0.01159 -0.0826 0.8801 0.7266
-2.250 0.0560 0.01588 0.01192 -0.0824 0.8784 0.7540
-2.000 0.0842 0.01625 0.01226 -0.0820 0.8771 0.7697
-1.750 0.1105 0.01675 0.01277 -0.0808 0.8760 0.7855
-1.500 0.1314 0.01748 0.01355 -0.0778 0.8749 0.8030
-1.250 0.1206 0.01811 0.01426 -0.0696 0.8652 0.8108
-1.000 0.1482 0.01834 0.01446 -0.0692 0.8631 0.8210
-0.750 0.1754 0.01819 0.01430 -0.0684 0.8615 0.8245
-0.500 0.2081 0.01802 0.01409 -0.0691 0.8604 0.8268
-0.250 0.2432 0.01782 0.01387 -0.0705 0.8596 0.8286
0.000 0.2793 0.01762 0.01364 -0.0722 0.8589 0.8302
0.250 0.3164 0.01739 0.01339 -0.0742 0.8583 0.8315
0.500 0.3555 0.01712 0.01310 -0.0765 0.8577 0.8327
0.750 0.3614 0.01726 0.01323 -0.0729 0.8462 0.8353
1.000 0.3999 0.01688 0.01284 -0.0751 0.8452 0.8362
1.250 0.4396 0.01642 0.01238 -0.0775 0.8443 0.8370
1.500 0.4815 0.01586 0.01181 -0.0802 0.8436 0.8376
1.750 0.5244 0.01514 0.01109 -0.0829 0.8431 0.8381
2.000 0.5720 0.01429 0.01025 -0.0866 0.8428 0.8383
2.250 0.6162 0.01344 0.00943 -0.0895 0.8407 0.8388
2.500 0.6231 0.01307 0.00909 -0.0851 0.8298 0.8403
2.750 0.6749 0.01194 0.00796 -0.0894 0.8274 0.8403
3.000 0.6779 0.01193 0.00800 -0.0846 0.8154 0.8415
3.250 0.7092 0.01140 0.00748 -0.0851 0.8094 0.8422
3.500 0.7156 0.01181 0.00796 -0.0814 0.7910 0.8437
3.750 0.7411 0.01155 0.00771 -0.0809 0.7734 0.8443
4.000 0.7905 0.01030 0.00635 -0.0844 0.7451 0.8443
4.250 0.8238 0.01007 0.00570 -0.0851 0.6698 0.8446
4.500 0.8328 0.01072 0.00601 -0.0816 0.6102 0.8454
4.750 0.8365 0.01153 0.00650 -0.0774 0.5412 0.8465
5.000 0.8396 0.01245 0.00707 -0.0733 0.4715 0.8478
5.250 0.8463 0.01337 0.00763 -0.0700 0.4022 0.8485
5.500 0.8567 0.01422 0.00815 -0.0675 0.3349 0.8491
5.750 0.8695 0.01503 0.00864 -0.0654 0.2725 0.8497
6.000 0.8840 0.01580 0.00912 -0.0637 0.2173 0.8502
6.250 0.9000 0.01652 0.00959 -0.0623 0.1711 0.8507
6.500 0.9172 0.01719 0.01005 -0.0610 0.1360 0.8512
6.750 0.9353 0.01781 0.01053 -0.0599 0.1120 0.8517
7.000 0.9543 0.01838 0.01101 -0.0589 0.0975 0.8525
7.250 0.9737 0.01891 0.01150 -0.0580 0.0883 0.8531
7.500 0.9929 0.01945 0.01202 -0.0571 0.0819 0.8535
7.750 1.0115 0.02004 0.01257 -0.0561 0.0769 0.8539
8.000 1.0316 0.02051 0.01308 -0.0553 0.0728 0.8543
8.250 1.0492 0.02116 0.01370 -0.0542 0.0696 0.8547
8.500 1.0687 0.02165 0.01424 -0.0533 0.0667 0.8551
8.750 1.0847 0.02233 0.01491 -0.0519 0.0643 0.8556
9.000 1.1027 0.02290 0.01554 -0.0509 0.0622 0.8562
9.250 1.1206 0.02348 0.01616 -0.0498 0.0601 0.8567
9.500 1.1346 0.02433 0.01700 -0.0482 0.0583 0.8573
9.750 1.1528 0.02489 0.01766 -0.0472 0.0568 0.8579
10.000 1.1694 0.02556 0.01838 -0.0460 0.0553 0.8585
10.250 1.1847 0.02633 0.01916 -0.0447 0.0540 0.8591
10.500 1.1990 0.02722 0.02008 -0.0432 0.0527 0.8598
10.750 1.2158 0.02790 0.02086 -0.0421 0.0514 0.8604
11.000 1.2316 0.02865 0.02168 -0.0409 0.0502 0.8611
11.250 1.2465 0.02948 0.02252 -0.0396 0.0491 0.8619
11.500 1.2605 0.03048 0.02355 -0.0382 0.0479 0.8629
11.750 1.2757 0.03124 0.02444 -0.0370 0.0467 0.8639
12.000 1.2906 0.03201 0.02528 -0.0359 0.0453 0.8649
12.250 1.3044 0.03292 0.02617 -0.0347 0.0441 0.8656
12.500 1.3175 0.03389 0.02726 -0.0334 0.0429 0.8665
12.750 1.3304 0.03481 0.02830 -0.0321 0.0417 0.8673
13.000 1.3433 0.03576 0.02931 -0.0309 0.0406 0.8682
13.250 1.3551 0.03686 0.03040 -0.0297 0.0396 0.8690
13.500 1.3658 0.03804 0.03172 -0.0283 0.0386 0.8699
13.750 1.3765 0.03916 0.03298 -0.0271 0.0374 0.8707
14.000 1.3868 0.04032 0.03420 -0.0259 0.0364 0.8715
14.250 1.3961 0.04165 0.03553 -0.0247 0.0355 0.8726
14.500 1.4037 0.04306 0.03715 -0.0233 0.0345 0.8738
14.750 1.4116 0.04446 0.03870 -0.0222 0.0334 0.8750
15.000 1.4193 0.04590 0.04020 -0.0211 0.0324 0.8763
15.250 1.4249 0.04761 0.04196 -0.0200 0.0315 0.8776
15.500 1.4311 0.04935 0.04392 -0.0191 0.0302 0.8791
15.750 1.4377 0.05108 0.04574 -0.0185 0.0291 0.8806
16.000 1.4418 0.05309 0.04777 -0.0177 0.0283 0.8822
16.250 1.4463 0.05523 0.05014 -0.0172 0.0270 0.8839
16.500 1.4518 0.05731 0.05232 -0.0169 0.0259 0.8856
16.750 1.4540 0.05978 0.05484 -0.0166 0.0250 0.8873
17.000 1.4561 0.06238 0.05765 -0.0164 0.0238 0.8893
17.250 1.4586 0.06497 0.06036 -0.0164 0.0227 0.8916
17.500 1.4574 0.06803 0.06349 -0.0166 0.0219 0.8941
17.750 1.4554 0.07134 0.06700 -0.0168 0.0209 0.8968
18.000 1.4544 0.07461 0.07041 -0.0173 0.0199 0.8999
18.250 1.4493 0.07855 0.07444 -0.0182 0.0192 0.9031
18.500 1.4408 0.08302 0.07908 -0.0192 0.0185 0.9071
18.750 1.4332 0.08746 0.08371 -0.0204 0.0177 0.9128
19.000 1.4235 0.09225 0.08866 -0.0219 0.0171 0.9202
19.250 1.4099 0.09736 0.09393 -0.0233 0.0167 0.9422
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