EPPLER 422 AIRFOIL (e422-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 422 AIRFOIL (e422-il) Reynolds number: 200,000 Max Cl/Cd: 60.01 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e422-il-200000.txt Download as CSV file: xf-e422-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 422 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.0711 0.09984 0.09597 -0.0808 0.7861 0.0440
-10.250 0.0657 0.09750 0.09354 -0.0830 0.7706 0.0451
-10.000 0.0636 0.09479 0.09076 -0.0843 0.7552 0.0454
-9.750 0.0837 0.09149 0.08734 -0.0829 0.7371 0.0462
-9.500 0.0923 0.08901 0.08478 -0.0831 0.7234 0.0469
-9.250 0.0993 0.08651 0.08219 -0.0834 0.7122 0.0480
-9.000 0.1043 0.08386 0.07950 -0.0841 0.7012 0.0496
-8.750 0.0937 0.08140 0.07700 -0.0869 0.6947 0.0512
-8.500 0.0808 0.08799 0.08347 -0.0926 0.7188 0.0500
-8.250 0.0603 0.08587 0.08137 -0.0976 0.7092 0.0515
-8.000 0.0785 0.08302 0.07842 -0.0959 0.6970 0.0519
-7.750 0.0948 0.08079 0.07613 -0.0948 0.6849 0.0529
-7.500 0.1037 0.07874 0.07400 -0.0949 0.6756 0.0541
-7.250 0.1089 0.07655 0.07182 -0.0954 0.6658 0.0560
-7.000 0.0857 0.07427 0.06956 -0.0998 0.6600 0.0583
-6.750 0.0949 0.07137 0.06666 -0.0994 0.6518 0.0589
-6.500 0.1107 0.06947 0.06470 -0.0976 0.6437 0.0600
-6.250 0.1207 0.06750 0.06268 -0.0980 0.6370 0.0611
-6.000 0.1285 0.06517 0.06036 -0.0996 0.6300 0.0635
-5.750 0.1310 0.06034 0.05550 -0.1081 0.6252 0.0669
-5.500 0.1167 0.03423 0.02862 -0.1285 0.6267 0.0343
-5.250 0.1340 0.03056 0.02455 -0.1297 0.6214 0.0329
-5.000 0.1492 0.02467 0.01730 -0.1304 0.6160 0.0304
-4.750 0.1723 0.02300 0.01530 -0.1299 0.6094 0.0305
-4.500 0.1970 0.02179 0.01384 -0.1294 0.6038 0.0312
-4.250 0.2220 0.02089 0.01281 -0.1289 0.5975 0.0324
-4.000 0.2482 0.02021 0.01175 -0.1283 0.5915 0.0347
-3.750 0.2738 0.01938 0.01090 -0.1280 0.5866 0.0369
-3.500 0.3002 0.01872 0.01007 -0.1274 0.5817 0.0389
-3.250 0.3257 0.01799 0.00934 -0.1268 0.5762 0.0414
-3.000 0.3521 0.01743 0.00869 -0.1262 0.5713 0.0458
-2.750 0.3790 0.01698 0.00819 -0.1259 0.5670 0.0557
-2.500 0.4051 0.01640 0.00774 -0.1254 0.5622 0.0859
-2.250 0.4323 0.01640 0.00786 -0.1251 0.5574 0.1328
-2.000 0.4599 0.01663 0.00802 -0.1249 0.5532 0.1565
-1.750 0.4878 0.01692 0.00822 -0.1248 0.5495 0.1757
-1.500 0.5146 0.01709 0.00835 -0.1244 0.5454 0.1917
-1.250 0.5411 0.01718 0.00838 -0.1240 0.5409 0.2059
-1.000 0.5681 0.01716 0.00837 -0.1237 0.5368 0.2192
-0.750 0.5956 0.01712 0.00826 -0.1235 0.5334 0.2312
-0.500 0.6241 0.01725 0.00823 -0.1235 0.5303 0.2438
-0.250 0.6497 0.01722 0.00831 -0.1230 0.5267 0.2556
0.000 0.6759 0.01720 0.00831 -0.1226 0.5228 0.2677
0.250 0.7029 0.01721 0.00829 -0.1223 0.5192 0.2813
0.500 0.7303 0.01722 0.00828 -0.1221 0.5160 0.2961
0.750 0.7584 0.01731 0.00833 -0.1221 0.5131 0.3124
1.000 0.7839 0.01740 0.00851 -0.1216 0.5100 0.3306
1.250 0.8091 0.01747 0.00869 -0.1211 0.5067 0.3532
1.500 0.8346 0.01747 0.00883 -0.1207 0.5033 0.3814
1.750 0.8606 0.01742 0.00892 -0.1203 0.5002 0.4280
2.000 0.8825 0.01665 0.00900 -0.1191 0.4975 0.7118
2.250 0.9392 0.01678 0.00917 -0.1248 0.4944 1.0000
2.500 0.9625 0.01707 0.00948 -0.1240 0.4913 1.0000
2.750 0.9868 0.01739 0.00977 -0.1234 0.4882 1.0000
3.000 1.0119 0.01767 0.01001 -0.1228 0.4851 1.0000
3.250 1.0381 0.01792 0.01018 -0.1225 0.4822 1.0000
3.500 1.0655 0.01819 0.01034 -0.1224 0.4797 1.0000
3.750 1.0934 0.01864 0.01066 -0.1224 0.4772 1.0000
4.000 1.1150 0.01901 0.01112 -0.1214 0.4744 1.0000
4.250 1.1375 0.01939 0.01156 -0.1206 0.4713 1.0000
4.500 1.1614 0.01973 0.01191 -0.1199 0.4682 1.0000
4.750 1.1867 0.02000 0.01215 -0.1195 0.4654 1.0000
5.000 1.2136 0.02029 0.01237 -0.1194 0.4630 1.0000
5.250 1.2415 0.02069 0.01270 -0.1195 0.4608 1.0000
5.500 1.2630 0.02122 0.01330 -0.1186 0.4581 1.0000
5.750 1.2829 0.02169 0.01387 -0.1174 0.4548 1.0000
6.000 1.3050 0.02208 0.01431 -0.1165 0.4516 1.0000
6.250 1.3291 0.02242 0.01467 -0.1160 0.4488 1.0000
6.500 1.3549 0.02273 0.01496 -0.1158 0.4464 1.0000
6.750 1.3833 0.02305 0.01521 -0.1160 0.4441 1.0000
7.000 1.4044 0.02363 0.01587 -0.1151 0.4413 1.0000
7.250 1.4208 0.02422 0.01660 -0.1135 0.4378 1.0000
7.500 1.4408 0.02467 0.01712 -0.1124 0.4344 1.0000
7.750 1.4647 0.02494 0.01741 -0.1118 0.4314 1.0000
8.000 1.4916 0.02515 0.01760 -0.1118 0.4288 1.0000
8.250 1.5228 0.02544 0.01780 -0.1125 0.4263 1.0000
8.500 1.5325 0.02616 0.01873 -0.1099 0.4225 1.0000
8.750 1.5479 0.02668 0.01939 -0.1081 0.4186 1.0000
9.000 1.5700 0.02693 0.01968 -0.1074 0.4152 1.0000
9.250 1.5971 0.02703 0.01976 -0.1073 0.4124 1.0000
9.500 1.6306 0.02717 0.01981 -0.1084 0.4097 1.0000
9.750 1.6343 0.02802 0.02091 -0.1050 0.4056 1.0000
10.000 1.6461 0.02856 0.02158 -0.1028 0.4015 1.0000
10.250 1.6682 0.02868 0.02173 -0.1020 0.3979 1.0000
10.500 1.7006 0.02851 0.02150 -0.1027 0.3948 1.0000
10.750 1.7168 0.02901 0.02209 -0.1012 0.3911 1.0000
11.000 1.7160 0.02983 0.02311 -0.0972 0.3866 1.0000
11.250 1.7315 0.03003 0.02337 -0.0955 0.3826 1.0000
11.500 1.7636 0.02976 0.02306 -0.0961 0.3791 1.0000
11.750 1.7767 0.03018 0.02356 -0.0941 0.3751 1.0000
12.000 1.7619 0.03119 0.02476 -0.0881 0.3707 1.0000
12.250 1.7722 0.03145 0.02508 -0.0857 0.3664 1.0000
12.500 1.8103 0.03087 0.02442 -0.0871 0.3624 1.0000
12.750 1.7936 0.03223 0.02598 -0.0816 0.3580 1.0000
13.000 1.7834 0.03346 0.02736 -0.0774 0.3531 1.0000
13.250 1.8076 0.03318 0.02705 -0.0769 0.3484 1.0000
13.500 1.8059 0.03431 0.02828 -0.0741 0.3436 1.0000
13.750 1.7863 0.03656 0.03070 -0.0703 0.3381 1.0000
14.000 1.8067 0.03649 0.03061 -0.0696 0.3330 1.0000
14.250 1.7903 0.03903 0.03331 -0.0669 0.3272 1.0000
14.500 1.7793 0.04141 0.03580 -0.0649 0.3209 1.0000
14.750 1.7972 0.04165 0.03600 -0.0642 0.3152 1.0000
15.000 1.7597 0.04674 0.04130 -0.0622 0.3078 1.0000
15.250 1.7878 0.04602 0.04049 -0.0617 0.3016 1.0000
15.500 1.7391 0.05297 0.04768 -0.0605 0.2934 1.0000
15.750 1.7588 0.05302 0.04766 -0.0600 0.2865 1.0000
16.000 1.7184 0.05993 0.05476 -0.0598 0.2777 1.0000
16.250 1.7202 0.06214 0.05697 -0.0595 0.2698 1.0000
16.500 1.7065 0.06635 0.06123 -0.0596 0.2611 1.0000
16.750 1.6897 0.07117 0.06612 -0.0600 0.2524 1.0000
17.000 1.7041 0.07184 0.06668 -0.0596 0.2443 1.0000
17.250 1.6734 0.07881 0.07380 -0.0606 0.2351 1.0000
17.500 1.6710 0.08192 0.07690 -0.0609 0.2266 1.0000
17.750 1.6688 0.08503 0.07998 -0.0612 0.2181 1.0000
18.000 1.6525 0.09029 0.08533 -0.0622 0.2097 1.0000
18.250 1.6607 0.09189 0.08681 -0.0622 0.2019 1.0000
18.500 1.6419 0.09775 0.09281 -0.0636 0.1939 1.0000
18.750 1.6437 0.10038 0.09539 -0.0640 0.1865 1.0000
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Polar data table (+)
Polar graphs
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