GOE 479 AIRFOIL (goe479-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 479 AIRFOIL (goe479-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.47 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe479-il-1000000.txt Download as CSV file: xf-goe479-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 479 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9373 0.03541 0.03277 -0.0926 1.0000 0.0206
-13.500 -0.9674 0.03371 0.03098 -0.0865 1.0000 0.0207
-13.250 -0.9784 0.03227 0.02945 -0.0824 1.0000 0.0208
-13.000 -0.9692 0.03086 0.02793 -0.0814 0.9992 0.0211
-12.750 -0.9441 0.02918 0.02609 -0.0835 0.9972 0.0215
-12.500 -0.9191 0.02758 0.02431 -0.0853 0.9952 0.0219
-12.250 -0.8920 0.02625 0.02283 -0.0869 0.9936 0.0223
-12.000 -0.8672 0.02533 0.02177 -0.0875 0.9910 0.0226
-11.750 -0.8481 0.02298 0.01918 -0.0884 0.9879 0.0232
-11.500 -0.8193 0.02222 0.01839 -0.0895 0.9862 0.0236
-11.250 -0.7882 0.02169 0.01783 -0.0907 0.9849 0.0240
-11.000 -0.7565 0.02113 0.01722 -0.0921 0.9838 0.0244
-10.750 -0.7247 0.02041 0.01641 -0.0935 0.9829 0.0249
-10.500 -0.7022 0.01963 0.01552 -0.0930 0.9786 0.0253
-10.250 -0.6727 0.01909 0.01488 -0.0938 0.9764 0.0259
-10.000 -0.6415 0.01855 0.01424 -0.0948 0.9747 0.0263
-9.750 -0.6096 0.01790 0.01347 -0.0960 0.9733 0.0266
-9.500 -0.5808 0.01618 0.01161 -0.0973 0.9718 0.0274
-9.250 -0.5480 0.01562 0.01103 -0.0986 0.9704 0.0279
-9.000 -0.5229 0.01527 0.01065 -0.0982 0.9655 0.0284
-8.750 -0.4934 0.01487 0.01020 -0.0986 0.9620 0.0290
-8.500 -0.4631 0.01438 0.00964 -0.0992 0.9588 0.0296
-8.250 -0.4316 0.01385 0.00903 -0.1001 0.9558 0.0301
-8.000 -0.4082 0.01345 0.00856 -0.0992 0.9489 0.0305
-7.750 -0.3794 0.01312 0.00815 -0.0993 0.9437 0.0309
-7.500 -0.3552 0.01219 0.00713 -0.0988 0.9376 0.0317
-7.250 -0.3302 0.01177 0.00669 -0.0982 0.9300 0.0324
-7.000 -0.3032 0.01143 0.00630 -0.0979 0.9224 0.0329
-6.750 -0.2778 0.01112 0.00595 -0.0973 0.9128 0.0335
-6.500 -0.2519 0.01082 0.00559 -0.0967 0.9031 0.0341
-6.250 -0.2256 0.01055 0.00524 -0.0962 0.8927 0.0348
-6.000 -0.2003 0.01029 0.00492 -0.0955 0.8803 0.0354
-5.750 -0.1740 0.01014 0.00470 -0.0950 0.8682 0.0359
-5.500 -0.1502 0.00962 0.00410 -0.0941 0.8555 0.0369
-5.250 -0.1251 0.00936 0.00379 -0.0934 0.8413 0.0378
-5.000 -0.0996 0.00919 0.00356 -0.0927 0.8257 0.0387
-4.750 -0.0741 0.00905 0.00334 -0.0920 0.8093 0.0397
-4.500 -0.0487 0.00892 0.00313 -0.0913 0.7918 0.0407
-4.250 -0.0232 0.00884 0.00296 -0.0907 0.7744 0.0415
-4.000 0.0013 0.00861 0.00265 -0.0898 0.7578 0.0432
-3.750 0.0267 0.00850 0.00248 -0.0892 0.7430 0.0449
-3.500 0.0527 0.00841 0.00234 -0.0886 0.7298 0.0466
-3.250 0.0791 0.00835 0.00223 -0.0881 0.7179 0.0482
-3.000 0.1046 0.00819 0.00202 -0.0875 0.7069 0.0513
-2.750 0.1308 0.00812 0.00191 -0.0870 0.6962 0.0544
-2.500 0.1573 0.00801 0.00179 -0.0865 0.6871 0.0585
-2.250 0.1835 0.00794 0.00170 -0.0861 0.6782 0.0640
-2.000 0.2101 0.00782 0.00160 -0.0857 0.6703 0.0728
-1.750 0.2361 0.00771 0.00152 -0.0852 0.6620 0.0896
-1.500 0.2623 0.00755 0.00147 -0.0847 0.6543 0.1234
-1.250 0.2884 0.00745 0.00144 -0.0843 0.6464 0.1530
-1.000 0.3150 0.00736 0.00141 -0.0839 0.6395 0.1801
-0.750 0.3414 0.00727 0.00139 -0.0835 0.6319 0.2118
-0.500 0.3673 0.00717 0.00139 -0.0831 0.6243 0.2524
-0.250 0.3932 0.00704 0.00138 -0.0826 0.6151 0.3012
0.000 0.4181 0.00686 0.00138 -0.0819 0.6055 0.3762
0.250 0.4404 0.00652 0.00141 -0.0809 0.5946 0.5210
0.500 0.4623 0.00617 0.00145 -0.0796 0.5843 0.6593
0.750 0.4819 0.00588 0.00150 -0.0776 0.5751 0.7874
1.000 0.5411 0.00566 0.00167 -0.0841 0.5626 0.9655
1.250 0.5893 0.00580 0.00175 -0.0884 0.5492 0.9853
1.500 0.6289 0.00592 0.00179 -0.0909 0.5362 0.9923
1.750 0.6703 0.00604 0.00183 -0.0938 0.5209 0.9972
2.000 0.7090 0.00616 0.00187 -0.0962 0.5039 1.0000
2.250 0.7315 0.00629 0.00192 -0.0950 0.4882 1.0000
2.500 0.7538 0.00644 0.00198 -0.0938 0.4720 1.0000
2.750 0.7759 0.00661 0.00206 -0.0925 0.4548 1.0000
3.000 0.7984 0.00677 0.00215 -0.0914 0.4418 1.0000
3.250 0.8208 0.00693 0.00225 -0.0902 0.4295 1.0000
3.500 0.8439 0.00707 0.00234 -0.0891 0.4179 1.0000
3.750 0.8669 0.00722 0.00245 -0.0881 0.4065 1.0000
4.000 0.8897 0.00739 0.00256 -0.0870 0.3961 1.0000
4.250 0.9128 0.00754 0.00267 -0.0860 0.3844 1.0000
4.500 0.9356 0.00771 0.00279 -0.0849 0.3703 1.0000
4.750 0.9584 0.00789 0.00292 -0.0838 0.3572 1.0000
5.000 0.9806 0.00810 0.00307 -0.0827 0.3403 1.0000
5.250 1.0019 0.00837 0.00323 -0.0814 0.3196 1.0000
5.500 1.0222 0.00869 0.00343 -0.0799 0.2926 1.0000
5.750 1.0417 0.00907 0.00367 -0.0783 0.2668 1.0000
6.000 1.0608 0.00946 0.00393 -0.0767 0.2425 1.0000
6.250 1.0803 0.00983 0.00420 -0.0751 0.2218 1.0000
6.500 1.0993 0.01023 0.00449 -0.0735 0.2001 1.0000
6.750 1.1165 0.01072 0.00483 -0.0715 0.1721 1.0000
7.000 1.1278 0.01154 0.00535 -0.0686 0.1247 1.0000
7.250 1.1291 0.01290 0.00626 -0.0641 0.0545 1.0000
7.500 1.1459 0.01337 0.00670 -0.0621 0.0466 1.0000
7.750 1.1629 0.01381 0.00712 -0.0601 0.0427 1.0000
8.000 1.1806 0.01412 0.00746 -0.0583 0.0413 1.0000
8.250 1.1968 0.01446 0.00781 -0.0562 0.0401 1.0000
8.500 1.2123 0.01484 0.00820 -0.0540 0.0389 1.0000
8.750 1.2267 0.01529 0.00867 -0.0516 0.0374 1.0000
9.000 1.2394 0.01585 0.00926 -0.0491 0.0360 1.0000
9.250 1.2558 0.01624 0.00969 -0.0473 0.0356 1.0000
9.500 1.2719 0.01667 0.01015 -0.0454 0.0351 1.0000
9.750 1.2870 0.01715 0.01067 -0.0435 0.0345 1.0000
10.000 1.3017 0.01768 0.01124 -0.0416 0.0339 1.0000
10.250 1.3161 0.01823 0.01182 -0.0398 0.0332 1.0000
10.500 1.3294 0.01886 0.01248 -0.0378 0.0325 1.0000
10.750 1.3411 0.01960 0.01326 -0.0358 0.0318 1.0000
11.000 1.3501 0.02053 0.01423 -0.0335 0.0312 1.0000
11.250 1.3529 0.02187 0.01566 -0.0307 0.0304 1.0000
11.500 1.3663 0.02262 0.01645 -0.0292 0.0302 1.0000
11.750 1.3800 0.02337 0.01726 -0.0279 0.0298 1.0000
12.000 1.3911 0.02434 0.01828 -0.0264 0.0294 1.0000
12.250 1.4015 0.02539 0.01938 -0.0250 0.0290 1.0000
12.500 1.4111 0.02655 0.02060 -0.0236 0.0286 1.0000
12.750 1.4219 0.02766 0.02176 -0.0224 0.0280 1.0000
13.000 1.4302 0.02903 0.02317 -0.0213 0.0276 1.0000
13.250 1.4376 0.03051 0.02470 -0.0202 0.0272 1.0000
13.500 1.4432 0.03223 0.02647 -0.0191 0.0267 1.0000
13.750 1.4438 0.03446 0.02877 -0.0181 0.0262 1.0000
14.000 1.4383 0.03736 0.03176 -0.0170 0.0258 1.0000
14.250 1.4415 0.03952 0.03400 -0.0164 0.0255 1.0000
14.500 1.4507 0.04116 0.03571 -0.0161 0.0252 1.0000
14.750 1.4563 0.04318 0.03780 -0.0157 0.0249 1.0000
15.000 1.4609 0.04535 0.04005 -0.0155 0.0246 1.0000
15.250 1.4646 0.04766 0.04243 -0.0153 0.0243 1.0000
15.500 1.4681 0.05006 0.04490 -0.0152 0.0239 1.0000
15.750 1.4697 0.05269 0.04760 -0.0152 0.0236 1.0000
16.000 1.4720 0.05528 0.05026 -0.0153 0.0232 1.0000
16.250 1.4733 0.05806 0.05309 -0.0155 0.0229 1.0000
16.500 1.4742 0.06094 0.05602 -0.0158 0.0225 1.0000
16.750 1.4719 0.06423 0.05938 -0.0162 0.0223 1.0000
17.000 1.4656 0.06803 0.06325 -0.0167 0.0220 1.0000
17.250 1.4521 0.07272 0.06802 -0.0173 0.0215 1.0000
17.500 1.4512 0.07604 0.07143 -0.0179 0.0213 1.0000
17.750 1.4510 0.07931 0.07478 -0.0187 0.0211 1.0000
18.000 1.4499 0.08276 0.07832 -0.0195 0.0209 1.0000
18.250 1.4495 0.08618 0.08183 -0.0205 0.0206 1.0000
18.500 1.4450 0.09009 0.08582 -0.0215 0.0204 1.0000
18.750 1.4415 0.09393 0.08974 -0.0226 0.0201 1.0000
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Polar data table (+)
Polar graphs
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