GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 573 AIRFOIL (goe573-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.67 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe573-il-1000000-n5.txt Download as CSV file: xf-goe573-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 573 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.2359 0.15724 0.15548 -0.0472 0.9839 0.0048
-15.000 -0.2428 0.15509 0.15337 -0.0444 0.9736 0.0048
-11.000 -0.4713 0.02282 0.01868 -0.1255 0.6682 0.0138
-9.500 -0.3611 0.01880 0.01390 -0.1168 0.6070 0.0165
-9.250 -0.3456 0.01760 0.01244 -0.1148 0.5995 0.0171
-9.000 -0.3245 0.01721 0.01196 -0.1136 0.5922 0.0174
-8.750 -0.2994 0.01727 0.01201 -0.1130 0.5848 0.0177
-8.500 -0.2759 0.01718 0.01185 -0.1121 0.5776 0.0179
-8.250 -0.2515 0.01710 0.01175 -0.1114 0.5708 0.0182
-8.000 -0.2275 0.01706 0.01165 -0.1106 0.5634 0.0185
-7.750 -0.2021 0.01715 0.01172 -0.1101 0.5567 0.0189
-7.500 -0.1811 0.01665 0.01108 -0.1088 0.5490 0.0193
-7.250 -0.1597 0.01615 0.01043 -0.1076 0.5419 0.0199
-7.000 -0.1386 0.01559 0.00971 -0.1063 0.5336 0.0204
-6.750 -0.1165 0.01515 0.00913 -0.1052 0.5270 0.0208
-6.500 -0.0932 0.01486 0.00872 -0.1043 0.5194 0.0211
-6.250 -0.0725 0.01421 0.00792 -0.1030 0.5129 0.0215
-6.000 -0.0488 0.01401 0.00766 -0.1021 0.5059 0.0219
-5.750 -0.0249 0.01392 0.00752 -0.1013 0.4990 0.0222
-5.500 -0.0008 0.01376 0.00730 -0.1005 0.4927 0.0225
-5.250 0.0229 0.01356 0.00702 -0.0996 0.4860 0.0229
-5.000 0.0469 0.01333 0.00672 -0.0988 0.4805 0.0233
-4.750 0.0707 0.01308 0.00638 -0.0980 0.4743 0.0237
-4.250 0.1182 0.01247 0.00558 -0.0962 0.4628 0.0245
-4.000 0.1421 0.01217 0.00520 -0.0954 0.4578 0.0248
-3.750 0.1659 0.01194 0.00489 -0.0945 0.4530 0.0252
-3.500 0.1904 0.01172 0.00461 -0.0938 0.4494 0.0254
-3.250 0.2148 0.01153 0.00437 -0.0930 0.4456 0.0257
-3.000 0.2393 0.01141 0.00419 -0.0923 0.4417 0.0259
-2.750 0.2624 0.01112 0.00384 -0.0913 0.4380 0.0264
-2.500 0.2857 0.01085 0.00353 -0.0903 0.4352 0.0269
-2.250 0.3098 0.01069 0.00334 -0.0895 0.4324 0.0273
-2.000 0.3337 0.01055 0.00318 -0.0887 0.4295 0.0277
-1.750 0.3575 0.01044 0.00304 -0.0878 0.4265 0.0280
-1.500 0.3813 0.01035 0.00292 -0.0869 0.4237 0.0283
-1.250 0.4050 0.01028 0.00283 -0.0861 0.4208 0.0288
-1.000 0.4293 0.01019 0.00271 -0.0853 0.4188 0.0293
-0.750 0.4534 0.01011 0.00263 -0.0845 0.4163 0.0297
-0.500 0.4774 0.01005 0.00255 -0.0837 0.4141 0.0302
-0.250 0.5013 0.01001 0.00249 -0.0829 0.4117 0.0309
0.000 0.5251 0.00999 0.00244 -0.0820 0.4095 0.0315
0.250 0.5486 0.00998 0.00241 -0.0811 0.4072 0.0320
0.500 0.5720 0.00995 0.00237 -0.0802 0.4052 0.0326
0.750 0.5959 0.00990 0.00232 -0.0794 0.4040 0.0341
1.000 0.6199 0.00987 0.00231 -0.0786 0.4024 0.0354
1.250 0.6436 0.00986 0.00231 -0.0778 0.4007 0.0368
1.500 0.6670 0.00986 0.00231 -0.0769 0.3990 0.0387
1.750 0.6896 0.00987 0.00232 -0.0758 0.3970 0.0413
2.000 0.7116 0.00987 0.00234 -0.0747 0.3950 0.0485
2.500 0.7533 0.00982 0.00245 -0.0719 0.3912 0.1224
2.750 0.7733 0.00973 0.00251 -0.0704 0.3896 0.1948
3.000 0.7802 0.00901 0.00269 -0.0663 0.3885 0.5764
3.500 1.0182 0.00938 0.00394 -0.1076 0.3797 0.9890
3.750 1.0541 0.00952 0.00404 -0.1097 0.3770 0.9913
4.000 1.0857 0.00967 0.00416 -0.1108 0.3744 0.9933
4.250 1.1104 0.00974 0.00425 -0.1103 0.3726 0.9941
4.500 1.1370 0.00981 0.00431 -0.1103 0.3708 0.9945
4.750 1.1637 0.00988 0.00440 -0.1104 0.3692 0.9949
5.000 1.1889 0.00997 0.00448 -0.1101 0.3674 0.9953
5.250 1.2139 0.01006 0.00458 -0.1098 0.3656 0.9957
5.500 1.2385 0.01016 0.00469 -0.1094 0.3638 0.9962
5.750 1.2625 0.01029 0.00481 -0.1089 0.3616 0.9968
6.000 1.2865 0.01041 0.00494 -0.1085 0.3596 0.9973
6.250 1.3116 0.01048 0.00504 -0.1082 0.3565 0.9978
6.500 1.3356 0.01060 0.00516 -0.1077 0.3511 0.9983
6.750 1.3584 0.01074 0.00530 -0.1071 0.3474 0.9989
7.000 1.3814 0.01087 0.00544 -0.1064 0.3428 0.9994
7.250 1.4044 0.01100 0.00558 -0.1058 0.3367 0.9999
7.500 1.4189 0.01119 0.00574 -0.1034 0.3295 1.0000
7.750 1.4322 0.01135 0.00590 -0.1007 0.3212 1.0000
8.000 1.4431 0.01159 0.00611 -0.0976 0.3109 1.0000
8.250 1.4528 0.01187 0.00636 -0.0942 0.2997 1.0000
8.500 1.4587 0.01230 0.00671 -0.0903 0.2818 1.0000
8.750 1.4585 0.01293 0.00722 -0.0852 0.2600 1.0000
9.000 1.4551 0.01372 0.00787 -0.0798 0.2351 1.0000
9.250 1.4561 0.01441 0.00849 -0.0752 0.2187 1.0000
9.500 1.4496 0.01542 0.00938 -0.0697 0.1942 1.0000
9.750 1.4403 0.01665 0.01047 -0.0640 0.1669 1.0000
10.000 1.4109 0.01897 0.01254 -0.0560 0.1213 1.0000
10.250 1.3799 0.02191 0.01531 -0.0492 0.0791 1.0000
10.500 1.3518 0.02530 0.01857 -0.0440 0.0404 1.0000
10.750 1.3386 0.02812 0.02135 -0.0410 0.0204 1.0000
11.000 1.3401 0.03000 0.02326 -0.0394 0.0170 1.0000
11.250 1.3418 0.03194 0.02525 -0.0381 0.0149 1.0000
11.500 1.3449 0.03384 0.02721 -0.0369 0.0138 1.0000
11.750 1.3463 0.03598 0.02940 -0.0358 0.0128 1.0000
12.000 1.3469 0.03823 0.03172 -0.0348 0.0121 1.0000
12.250 1.3455 0.04073 0.03428 -0.0338 0.0111 1.0000
12.500 1.3459 0.04313 0.03674 -0.0330 0.0108 1.0000
12.750 1.3454 0.04563 0.03931 -0.0323 0.0102 1.0000
13.000 1.3451 0.04817 0.04191 -0.0316 0.0099 1.0000
13.250 1.3428 0.05098 0.04479 -0.0310 0.0096 1.0000
13.500 1.3398 0.05393 0.04780 -0.0305 0.0089 1.0000
13.750 1.3362 0.05696 0.05090 -0.0300 0.0086 1.0000
14.000 1.3323 0.06011 0.05412 -0.0296 0.0083 1.0000
14.250 1.3298 0.06315 0.05723 -0.0294 0.0081 1.0000
14.500 1.3281 0.06616 0.06030 -0.0291 0.0079 1.0000
14.750 1.3263 0.06916 0.06337 -0.0290 0.0076 1.0000
15.000 1.3240 0.07226 0.06654 -0.0289 0.0073 1.0000
15.250 1.3213 0.07549 0.06983 -0.0289 0.0071 1.0000
15.500 1.3186 0.07873 0.07314 -0.0289 0.0070 1.0000
15.750 1.3166 0.08190 0.07637 -0.0290 0.0069 1.0000
16.000 1.3132 0.08528 0.07980 -0.0291 0.0066 1.0000
16.250 1.3107 0.08856 0.08314 -0.0293 0.0064 1.0000
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