GOE 423 AIRFOIL (goe423-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 423 AIRFOIL (goe423-il) Reynolds number: 500,000 Max Cl/Cd: 101.12 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe423-il-500000-n5.txt Download as CSV file: xf-goe423-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 423 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8045 0.04392 0.04008 -0.1241 0.9821 0.0386
-15.000 -0.8121 0.03911 0.03506 -0.1291 0.9736 0.0388
-14.750 -0.8095 0.03631 0.03214 -0.1314 0.9656 0.0390
-14.500 -0.8055 0.03428 0.03000 -0.1320 0.9563 0.0392
-14.250 -0.8008 0.03275 0.02837 -0.1315 0.9468 0.0393
-14.000 -0.7934 0.03154 0.02708 -0.1306 0.9388 0.0395
-13.750 -0.7854 0.03051 0.02596 -0.1293 0.9298 0.0398
-13.500 -0.7760 0.02961 0.02497 -0.1278 0.9210 0.0400
-13.250 -0.7674 0.02876 0.02402 -0.1259 0.9100 0.0403
-13.000 -0.7557 0.02788 0.02302 -0.1244 0.9002 0.0406
-12.750 -0.7427 0.02694 0.02194 -0.1230 0.8899 0.0408
-12.500 -0.7281 0.02604 0.02089 -0.1218 0.8777 0.0412
-12.250 -0.7123 0.02515 0.01984 -0.1206 0.8667 0.0415
-12.000 -0.6955 0.02430 0.01881 -0.1195 0.8560 0.0418
-11.750 -0.6773 0.02349 0.01784 -0.1186 0.8455 0.0422
-11.500 -0.6583 0.02276 0.01693 -0.1177 0.8351 0.0427
-11.250 -0.6383 0.02209 0.01609 -0.1168 0.8237 0.0431
-11.000 -0.6176 0.02146 0.01528 -0.1160 0.8127 0.0434
-10.750 -0.5968 0.02081 0.01447 -0.1152 0.8006 0.0436
-10.500 -0.5757 0.02010 0.01367 -0.1145 0.7868 0.0440
-10.250 -0.5537 0.01958 0.01304 -0.1138 0.7707 0.0443
-10.000 -0.5315 0.01915 0.01249 -0.1131 0.7500 0.0446
-9.750 -0.5095 0.01879 0.01198 -0.1122 0.7219 0.0449
-9.500 -0.4881 0.01850 0.01149 -0.1113 0.6884 0.0452
-9.250 -0.4660 0.01822 0.01104 -0.1104 0.6638 0.0456
-9.000 -0.4430 0.01793 0.01062 -0.1097 0.6479 0.0461
-8.750 -0.4195 0.01763 0.01019 -0.1091 0.6364 0.0466
-8.500 -0.3956 0.01730 0.00975 -0.1086 0.6274 0.0471
-8.250 -0.3716 0.01696 0.00930 -0.1080 0.6200 0.0475
-8.000 -0.3470 0.01661 0.00887 -0.1076 0.6139 0.0479
-7.750 -0.3223 0.01630 0.00846 -0.1071 0.6082 0.0484
-7.250 -0.2722 0.01575 0.00774 -0.1063 0.5987 0.0490
-7.000 -0.2478 0.01532 0.00728 -0.1058 0.5944 0.0496
-6.750 -0.2230 0.01500 0.00693 -0.1053 0.5900 0.0501
-6.500 -0.1979 0.01477 0.00666 -0.1049 0.5858 0.0507
-6.250 -0.1725 0.01457 0.00641 -0.1045 0.5822 0.0513
-6.000 -0.1464 0.01434 0.00616 -0.1043 0.5793 0.0520
-5.750 -0.1204 0.01412 0.00591 -0.1040 0.5763 0.0526
-5.500 -0.0945 0.01391 0.00566 -0.1037 0.5732 0.0533
-5.250 -0.0686 0.01371 0.00543 -0.1034 0.5702 0.0539
-5.000 -0.0426 0.01355 0.00521 -0.1030 0.5674 0.0545
-4.750 -0.0167 0.01340 0.00501 -0.1027 0.5647 0.0551
-4.500 0.0090 0.01318 0.00477 -0.1023 0.5624 0.0558
-4.250 0.0352 0.01296 0.00456 -0.1021 0.5603 0.0567
-4.000 0.0616 0.01280 0.00440 -0.1019 0.5580 0.0577
-3.750 0.0882 0.01266 0.00426 -0.1017 0.5557 0.0588
-3.500 0.1148 0.01254 0.00412 -0.1014 0.5534 0.0600
-3.250 0.1413 0.01244 0.00399 -0.1012 0.5510 0.0612
-3.000 0.1679 0.01235 0.00387 -0.1010 0.5486 0.0621
-2.750 0.1940 0.01223 0.00373 -0.1007 0.5463 0.0637
-2.500 0.2204 0.01214 0.00364 -0.1005 0.5442 0.0654
-2.250 0.2475 0.01204 0.00355 -0.1003 0.5427 0.0673
-2.000 0.2747 0.01196 0.00348 -0.1002 0.5410 0.0695
-1.750 0.3016 0.01186 0.00340 -0.1001 0.5392 0.0728
-1.500 0.3286 0.01178 0.00334 -0.1000 0.5374 0.0772
-1.250 0.3554 0.01170 0.00329 -0.0998 0.5356 0.0838
-1.000 0.3821 0.01160 0.00326 -0.0997 0.5339 0.0969
-0.750 0.4086 0.01151 0.00326 -0.0995 0.5322 0.1207
-0.500 0.4354 0.01147 0.00325 -0.0994 0.5306 0.1386
-0.250 0.4623 0.01143 0.00325 -0.0993 0.5290 0.1535
0.000 0.4891 0.01140 0.00326 -0.0992 0.5274 0.1690
0.250 0.5158 0.01135 0.00328 -0.0991 0.5257 0.1916
0.500 0.5421 0.01120 0.00331 -0.0989 0.5243 0.2427
0.750 0.5682 0.01104 0.00335 -0.0988 0.5228 0.3014
1.000 0.5917 0.01063 0.00339 -0.0982 0.5214 0.4396
1.250 0.6152 0.01033 0.00348 -0.0976 0.5200 0.5704
1.500 0.6392 0.01011 0.00355 -0.0969 0.5185 0.6512
1.750 0.6584 0.00971 0.00370 -0.0949 0.5172 0.8082
2.000 0.6933 0.00969 0.00394 -0.0960 0.5157 0.9210
2.250 0.7376 0.00986 0.00412 -0.0995 0.5143 0.9534
2.500 0.7738 0.01000 0.00423 -0.1014 0.5127 0.9666
2.750 0.8110 0.01014 0.00435 -0.1035 0.5111 0.9753
3.000 0.8469 0.01029 0.00447 -0.1054 0.5095 0.9828
3.250 0.8867 0.01045 0.00460 -0.1082 0.5077 0.9884
3.500 0.9225 0.01053 0.00470 -0.1101 0.5051 0.9932
3.750 0.9620 0.01060 0.00478 -0.1128 0.5012 0.9969
4.000 0.9989 0.01069 0.00486 -0.1150 0.4969 1.0000
4.250 1.0178 0.01078 0.00490 -0.1133 0.4924 1.0000
4.500 1.0372 0.01085 0.00498 -0.1117 0.4879 1.0000
4.750 1.0568 0.01090 0.00505 -0.1101 0.4830 1.0000
5.000 1.0747 0.01099 0.00512 -0.1082 0.4773 1.0000
5.250 1.0927 0.01109 0.00520 -0.1064 0.4723 1.0000
5.500 1.1127 0.01117 0.00532 -0.1049 0.4677 1.0000
5.750 1.1311 0.01127 0.00542 -0.1031 0.4625 1.0000
6.000 1.1472 0.01141 0.00554 -0.1009 0.4564 1.0000
6.250 1.1649 0.01152 0.00567 -0.0990 0.4487 1.0000
6.500 1.1777 0.01168 0.00580 -0.0961 0.4413 1.0000
6.750 1.1943 0.01183 0.00596 -0.0940 0.4306 1.0000
7.000 1.2069 0.01210 0.00618 -0.0913 0.4138 1.0000
7.250 1.2107 0.01271 0.00660 -0.0872 0.3791 1.0000
7.500 1.2073 0.01380 0.00743 -0.0821 0.3337 1.0000
7.750 1.2069 0.01497 0.00839 -0.0779 0.2980 1.0000
8.000 1.2093 0.01612 0.00939 -0.0744 0.2680 1.0000
8.250 1.2115 0.01735 0.01048 -0.0710 0.2385 1.0000
8.500 1.2116 0.01878 0.01176 -0.0676 0.2086 1.0000
8.750 1.1973 0.02115 0.01386 -0.0629 0.1574 1.0000
9.000 1.1790 0.02405 0.01651 -0.0583 0.1095 1.0000
9.250 1.1663 0.02686 0.01915 -0.0548 0.0680 1.0000
9.500 1.1619 0.02925 0.02146 -0.0524 0.0493 1.0000
9.750 1.1681 0.03093 0.02315 -0.0511 0.0447 1.0000
10.000 1.1753 0.03261 0.02485 -0.0499 0.0420 1.0000
10.250 1.1834 0.03426 0.02654 -0.0489 0.0404 1.0000
10.500 1.1918 0.03592 0.02825 -0.0480 0.0391 1.0000
10.750 1.1994 0.03771 0.03008 -0.0472 0.0380 1.0000
11.000 1.2063 0.03961 0.03202 -0.0464 0.0370 1.0000
11.250 1.2120 0.04165 0.03409 -0.0456 0.0361 1.0000
11.500 1.2190 0.04358 0.03607 -0.0449 0.0355 1.0000
11.750 1.2263 0.04549 0.03803 -0.0442 0.0349 1.0000
12.000 1.2329 0.04750 0.04010 -0.0436 0.0344 1.0000
12.250 1.2391 0.04955 0.04220 -0.0430 0.0340 1.0000
12.500 1.2449 0.05166 0.04435 -0.0424 0.0335 1.0000
12.750 1.2500 0.05384 0.04658 -0.0418 0.0331 1.0000
13.000 1.2548 0.05605 0.04884 -0.0413 0.0327 1.0000
13.250 1.2588 0.05839 0.05122 -0.0407 0.0323 1.0000
13.500 1.2623 0.06078 0.05366 -0.0402 0.0319 1.0000
13.750 1.2648 0.06331 0.05625 -0.0397 0.0316 1.0000
14.000 1.2663 0.06596 0.05894 -0.0392 0.0312 1.0000
14.250 1.2709 0.06830 0.06133 -0.0389 0.0309 1.0000
14.500 1.2754 0.07068 0.06378 -0.0386 0.0306 1.0000
14.750 1.2805 0.07301 0.06616 -0.0383 0.0303 1.0000
15.000 1.2841 0.07552 0.06874 -0.0381 0.0300 1.0000
15.250 1.2878 0.07803 0.07130 -0.0379 0.0297 1.0000
15.500 1.2915 0.08054 0.07387 -0.0377 0.0294 1.0000
15.750 1.2942 0.08322 0.07660 -0.0376 0.0292 1.0000
16.000 1.2977 0.08580 0.07924 -0.0375 0.0289 1.0000
16.250 1.3004 0.08849 0.08198 -0.0375 0.0286 1.0000
16.500 1.3032 0.09120 0.08475 -0.0375 0.0284 1.0000
16.750 1.3062 0.09383 0.08743 -0.0375 0.0281 1.0000
17.000 1.3082 0.09666 0.09030 -0.0376 0.0278 1.0000
17.250 1.3102 0.09947 0.09316 -0.0378 0.0276 1.0000
17.500 1.3117 0.10234 0.09607 -0.0380 0.0273 1.0000
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Polar data table (+)
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