GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 406 AIRFOIL (goe406-il) Reynolds number: 500,000 Max Cl/Cd: 89.28 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe406-il-500000-n5.txt Download as CSV file: xf-goe406-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 406 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1967 0.11714 0.11462 -0.0604 0.9851 0.0204
-11.250 -0.1876 0.11307 0.11053 -0.0642 0.9833 0.0204
-11.000 -0.1823 0.10973 0.10720 -0.0659 0.9793 0.0205
-10.750 -0.1723 0.10620 0.10368 -0.0684 0.9759 0.0205
-10.500 -0.1547 0.10351 0.10098 -0.0694 0.9734 0.0207
-10.250 -0.1454 0.10088 0.09837 -0.0704 0.9677 0.0209
-10.000 -0.1351 0.09787 0.09537 -0.0724 0.9616 0.0210
-9.750 -0.1246 0.09559 0.09309 -0.0735 0.9536 0.0218
-9.000 -0.0722 0.08228 0.07967 -0.0920 0.9048 0.0237
-8.750 -0.0237 0.07498 0.07221 -0.1089 0.8793 0.0238
-8.500 0.0183 0.06874 0.06570 -0.1231 0.8431 0.0239
-8.250 0.0296 0.06541 0.06217 -0.1270 0.8150 0.0239
-8.000 0.0429 0.06412 0.06078 -0.1264 0.7979 0.0242
-7.500 0.0497 0.06082 0.05736 -0.1250 0.7720 0.0248
-7.250 0.0496 0.05883 0.05533 -0.1245 0.7628 0.0251
-7.000 0.0518 0.05656 0.05301 -0.1245 0.7534 0.0255
-6.750 0.0549 0.05414 0.05053 -0.1244 0.7448 0.0257
-6.500 0.0541 0.05002 0.04626 -0.1255 0.7372 0.0275
-6.250 0.0593 0.04685 0.04296 -0.1249 0.7309 0.0276
-6.000 0.0659 0.04380 0.03979 -0.1238 0.7242 0.0276
-5.750 0.0738 0.04102 0.03686 -0.1222 0.7178 0.0276
-5.500 0.0825 0.03821 0.03389 -0.1204 0.7123 0.0277
-5.250 0.0919 0.03566 0.03120 -0.1183 0.7053 0.0277
-4.750 0.1189 0.03363 0.02909 -0.1153 0.6928 0.0269
-4.500 0.1303 0.03148 0.02679 -0.1130 0.6868 0.0259
-4.250 0.1401 0.02877 0.02385 -0.1100 0.6810 0.0253
-4.000 0.1490 0.02563 0.02041 -0.1064 0.6756 0.0248
-3.750 0.1558 0.02199 0.01636 -0.1019 0.6695 0.0245
-3.500 0.1728 0.02103 0.01523 -0.0998 0.6618 0.0248
-3.250 0.1898 0.01968 0.01369 -0.0975 0.6547 0.0251
-3.000 0.2052 0.01793 0.01163 -0.0947 0.6478 0.0252
-2.750 0.2234 0.01642 0.00982 -0.0925 0.6426 0.0252
-2.500 0.2445 0.01540 0.00858 -0.0909 0.6371 0.0254
-2.250 0.2666 0.01464 0.00762 -0.0895 0.6312 0.0255
-2.000 0.2897 0.01405 0.00689 -0.0883 0.6250 0.0260
-1.750 0.3134 0.01351 0.00621 -0.0873 0.6178 0.0261
-1.500 0.3366 0.01309 0.00565 -0.0862 0.6103 0.0264
-1.250 0.3611 0.01270 0.00518 -0.0853 0.6031 0.0266
-1.000 0.3846 0.01240 0.00478 -0.0842 0.5956 0.0269
-0.750 0.4089 0.01214 0.00444 -0.0833 0.5879 0.0273
-0.250 0.4545 0.01167 0.00385 -0.0810 0.5674 0.0281
0.000 0.4764 0.01147 0.00361 -0.0796 0.5564 0.0283
0.250 0.4974 0.01132 0.00342 -0.0781 0.5439 0.0287
0.500 0.5181 0.01122 0.00327 -0.0765 0.5287 0.0290
0.750 0.5379 0.01116 0.00315 -0.0747 0.5121 0.0294
1.000 0.5567 0.01115 0.00306 -0.0727 0.4932 0.0298
1.250 0.5746 0.01119 0.00301 -0.0705 0.4711 0.0304
1.500 0.5913 0.01128 0.00299 -0.0681 0.4475 0.0308
1.750 0.6068 0.01141 0.00301 -0.0655 0.4245 0.0313
2.000 0.6226 0.01154 0.00304 -0.0629 0.4042 0.0318
2.250 0.6393 0.01163 0.00306 -0.0606 0.3882 0.0329
2.500 0.6569 0.01174 0.00311 -0.0585 0.3753 0.0342
2.750 0.6755 0.01185 0.00317 -0.0565 0.3645 0.0353
3.000 0.6946 0.01196 0.00325 -0.0547 0.3558 0.0366
3.250 0.7139 0.01208 0.00334 -0.0529 0.3482 0.0384
3.500 0.7331 0.01221 0.00345 -0.0512 0.3418 0.0414
3.750 0.7534 0.01229 0.00360 -0.0497 0.3359 0.0725
4.250 1.0669 0.01214 0.00522 -0.1092 0.3119 1.0000
4.500 1.0874 0.01233 0.00540 -0.1078 0.3087 1.0000
4.750 1.1086 0.01249 0.00557 -0.1065 0.3058 1.0000
5.000 1.1292 0.01267 0.00574 -0.1050 0.3029 1.0000
5.250 1.1490 0.01287 0.00594 -0.1035 0.2998 1.0000
5.500 1.1680 0.01309 0.00615 -0.1018 0.2970 1.0000
5.750 1.1856 0.01333 0.00638 -0.0998 0.2942 1.0000
6.000 1.2031 0.01352 0.00658 -0.0978 0.2913 1.0000
6.250 1.2207 0.01369 0.00678 -0.0958 0.2891 1.0000
6.500 1.2376 0.01388 0.00698 -0.0937 0.2850 1.0000
6.750 1.2536 0.01412 0.00721 -0.0914 0.2809 1.0000
7.000 1.2676 0.01442 0.00748 -0.0888 0.2760 1.0000
7.250 1.2860 0.01459 0.00770 -0.0871 0.2728 1.0000
7.500 1.3035 0.01482 0.00796 -0.0852 0.2700 1.0000
7.750 1.3200 0.01507 0.00823 -0.0832 0.2663 1.0000
8.000 1.3359 0.01537 0.00853 -0.0811 0.2630 1.0000
8.250 1.3508 0.01570 0.00887 -0.0789 0.2599 1.0000
8.500 1.3688 0.01594 0.00917 -0.0772 0.2567 1.0000
8.750 1.3859 0.01622 0.00949 -0.0754 0.2525 1.0000
9.000 1.4012 0.01656 0.00985 -0.0734 0.2481 1.0000
9.250 1.4151 0.01698 0.01028 -0.0712 0.2436 1.0000
9.500 1.4323 0.01728 0.01064 -0.0695 0.2390 1.0000
9.750 1.4458 0.01774 0.01109 -0.0674 0.2309 1.0000
10.000 1.4601 0.01818 0.01155 -0.0654 0.2241 1.0000
10.250 1.4718 0.01875 0.01211 -0.0630 0.2143 1.0000
10.500 1.4842 0.01933 0.01269 -0.0609 0.2036 1.0000
10.750 1.4915 0.02018 0.01347 -0.0581 0.1863 1.0000
11.000 1.4821 0.02205 0.01504 -0.0534 0.1406 1.0000
11.250 1.4722 0.02415 0.01694 -0.0491 0.1104 1.0000
11.500 1.4713 0.02581 0.01854 -0.0461 0.0940 1.0000
11.750 1.4631 0.02812 0.02071 -0.0428 0.0645 1.0000
12.000 1.4583 0.03032 0.02284 -0.0401 0.0489 1.0000
12.250 1.4607 0.03204 0.02458 -0.0382 0.0432 1.0000
12.500 1.4632 0.03382 0.02639 -0.0365 0.0392 1.0000
12.750 1.4683 0.03543 0.02806 -0.0350 0.0370 1.0000
13.000 1.4713 0.03726 0.02995 -0.0335 0.0348 1.0000
13.250 1.4733 0.03924 0.03199 -0.0322 0.0331 1.0000
13.500 1.4772 0.04111 0.03394 -0.0310 0.0319 1.0000
13.750 1.4797 0.04315 0.03606 -0.0299 0.0306 1.0000
14.000 1.4805 0.04540 0.03838 -0.0288 0.0295 1.0000
14.250 1.4799 0.04788 0.04093 -0.0279 0.0286 1.0000
14.500 1.4772 0.05067 0.04379 -0.0270 0.0276 1.0000
14.750 1.4783 0.05309 0.04631 -0.0264 0.0266 1.0000
15.000 1.4775 0.05580 0.04912 -0.0258 0.0257 1.0000
15.250 1.4749 0.05882 0.05222 -0.0254 0.0251 1.0000
15.500 1.4707 0.06211 0.05560 -0.0251 0.0243 1.0000
15.750 1.4655 0.06561 0.05919 -0.0250 0.0240 1.0000
16.000 1.4576 0.06956 0.06324 -0.0250 0.0232 1.0000
16.250 1.4502 0.07355 0.06733 -0.0252 0.0228 1.0000
16.500 1.4444 0.07741 0.07130 -0.0255 0.0223 1.0000
16.750 1.4363 0.08167 0.07568 -0.0260 0.0219 1.0000
17.000 1.4277 0.08606 0.08017 -0.0266 0.0213 1.0000
17.250 1.4191 0.09053 0.08474 -0.0274 0.0208 1.0000
17.500 1.4093 0.09523 0.08955 -0.0283 0.0205 1.0000
17.750 1.3990 0.10005 0.09446 -0.0293 0.0201 1.0000
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