GOE 15K AIRFOIL (goe15k-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 15K AIRFOIL (goe15k-il) Reynolds number: 500,000 Max Cl/Cd: 92.82 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe15k-il-500000.txt Download as CSV file: xf-goe15k-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 15K 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7375 0.07494 0.07186 -0.1173 0.9701 0.0221
-15.750 -0.7632 0.06582 0.06253 -0.1247 0.9684 0.0226
-15.500 -0.7934 0.05625 0.05268 -0.1327 0.9669 0.0222
-15.250 -0.7989 0.05095 0.04716 -0.1382 0.9659 0.0226
-15.000 -0.8219 0.04643 0.04245 -0.1381 0.9601 0.0227
-14.750 -0.8344 0.04253 0.03831 -0.1387 0.9573 0.0227
-14.500 -0.8337 0.04009 0.03564 -0.1391 0.9558 0.0235
-14.250 -0.8294 0.03786 0.03323 -0.1391 0.9547 0.0234
-14.000 -0.8478 0.03561 0.03083 -0.1341 0.9484 0.0237
-13.750 -0.8391 0.03459 0.02981 -0.1328 0.9459 0.0245
-13.500 -0.8265 0.03352 0.02868 -0.1321 0.9444 0.0250
-13.250 -0.8125 0.03247 0.02752 -0.1314 0.9432 0.0257
-13.000 -0.7973 0.03150 0.02641 -0.1308 0.9423 0.0266
-12.750 -0.8090 0.03055 0.02535 -0.1243 0.9348 0.0266
-12.500 -0.7969 0.02956 0.02417 -0.1225 0.9327 0.0275
-12.250 -0.7854 0.02806 0.02251 -0.1209 0.9313 0.0282
-12.000 -0.7673 0.02717 0.02156 -0.1202 0.9304 0.0288
-11.750 -0.7433 0.02723 0.02165 -0.1201 0.9296 0.0300
-11.500 -0.7544 0.02722 0.02159 -0.1127 0.9217 0.0307
-11.250 -0.7394 0.02631 0.02054 -0.1109 0.9198 0.0314
-11.000 -0.7209 0.02581 0.01990 -0.1097 0.9186 0.0326
-10.750 -0.7020 0.02479 0.01879 -0.1088 0.9176 0.0339
-10.500 -0.6799 0.02459 0.01859 -0.1082 0.9169 0.0349
-10.250 -0.6908 0.02441 0.01834 -0.1006 0.9098 0.0354
-10.000 -0.6781 0.02444 0.01833 -0.0978 0.9070 0.0365
-9.750 -0.6589 0.02397 0.01774 -0.0964 0.9056 0.0380
-9.500 -0.6395 0.02373 0.01736 -0.0949 0.9045 0.0389
-9.250 -0.6131 0.02257 0.01618 -0.0954 0.9039 0.0407
-9.000 -0.5891 0.02211 0.01571 -0.0951 0.9033 0.0419
-8.750 -0.6061 0.02253 0.01608 -0.0858 0.8958 0.0424
-8.500 -0.5970 0.02245 0.01594 -0.0821 0.8928 0.0437
-8.250 -0.5811 0.02234 0.01573 -0.0798 0.8912 0.0454
-8.000 -0.5498 0.02133 0.01462 -0.0811 0.8907 0.0472
-7.750 -0.5248 0.02083 0.01415 -0.0809 0.8900 0.0492
-7.500 -0.4995 0.02047 0.01375 -0.0808 0.8894 0.0506
-7.250 -0.4733 0.02013 0.01335 -0.0807 0.8888 0.0526
-7.000 -0.4456 0.01979 0.01293 -0.0809 0.8883 0.0542
-6.750 -0.4095 0.01877 0.01188 -0.0833 0.8882 0.0568
-6.500 -0.4591 0.02003 0.01309 -0.0668 0.8766 0.0564
-6.250 -0.4312 0.01949 0.01255 -0.0673 0.8759 0.0582
-6.000 -0.4041 0.01908 0.01212 -0.0674 0.8752 0.0600
-5.750 -0.3763 0.01873 0.01174 -0.0677 0.8746 0.0619
-5.500 -0.4146 0.01984 0.01281 -0.0540 0.8653 0.0618
-5.250 -0.3997 0.01984 0.01277 -0.0514 0.8630 0.0636
-5.000 -0.3759 0.01964 0.01252 -0.0509 0.8618 0.0644
-4.750 -0.3481 0.01914 0.01199 -0.0512 0.8611 0.0665
-4.500 -0.3205 0.01871 0.01156 -0.0514 0.8603 0.0688
-4.250 -0.2919 0.01838 0.01123 -0.0518 0.8596 0.0716
-4.000 -0.2624 0.01808 0.01091 -0.0523 0.8591 0.0735
-3.750 -0.3037 0.01941 0.01220 -0.0382 0.8492 0.0732
-3.500 -0.2819 0.01932 0.01209 -0.0372 0.8474 0.0746
-3.250 -0.2551 0.01917 0.01190 -0.0371 0.8463 0.0766
-3.000 -0.2231 0.01877 0.01152 -0.0382 0.8456 0.0822
-2.750 -0.1907 0.01848 0.01125 -0.0393 0.8449 0.0869
-2.500 -0.1568 0.01809 0.01094 -0.0408 0.8444 0.1010
-2.250 -0.1216 0.01738 0.01070 -0.0429 0.8441 0.2009
-2.000 -0.0889 0.01690 0.01054 -0.0443 0.8436 0.2788
-1.750 -0.0948 0.01757 0.01127 -0.0377 0.8376 0.2986
-1.500 -0.0516 0.01699 0.01091 -0.0411 0.8390 0.3545
-1.250 -0.0127 0.01646 0.01059 -0.0436 0.8398 0.4140
-1.000 0.2424 0.01432 0.01036 -0.0938 0.8581 0.8931
-0.750 0.2796 0.01454 0.01055 -0.0955 0.8578 0.9166
-0.500 0.3257 0.01451 0.01048 -0.0992 0.8577 0.9296
-0.250 0.3497 0.01480 0.01075 -0.0983 0.8558 0.9395
0.000 0.4064 0.01493 0.01086 -0.1046 0.8555 0.9437
0.250 0.4567 0.01521 0.01111 -0.1094 0.8557 0.9525
0.500 0.5340 0.01486 0.01075 -0.1203 0.8574 0.9545
0.750 0.5929 0.01482 0.01071 -0.1273 0.8574 0.9585
1.000 0.6395 0.01483 0.01072 -0.1316 0.8571 0.9637
1.250 0.6862 0.01484 0.01075 -0.1360 0.8559 0.9664
1.500 0.6665 0.01599 0.01196 -0.1259 0.8466 0.9768
1.750 0.7393 0.01504 0.01101 -0.1357 0.8466 0.9783
2.000 0.8054 0.01426 0.01022 -0.1441 0.8453 0.9796
2.250 0.8974 0.01314 0.00905 -0.1584 0.8421 0.9777
2.500 0.9103 0.01313 0.00910 -0.1550 0.8345 0.9870
2.750 0.9723 0.01243 0.00838 -0.1626 0.8278 0.9890
3.000 1.0150 0.01174 0.00773 -0.1659 0.8180 0.9989
3.250 1.0541 0.01137 0.00735 -0.1686 0.8110 0.9999
3.500 1.0471 0.01153 0.00755 -0.1610 0.8038 1.0000
3.750 1.0628 0.01145 0.00748 -0.1584 0.7963 1.0000
4.000 1.0586 0.01160 0.00767 -0.1514 0.7873 1.0000
4.250 1.0697 0.01156 0.00763 -0.1478 0.7768 1.0000
4.500 1.0665 0.01172 0.00782 -0.1411 0.7650 1.0000
4.750 1.0629 0.01188 0.00796 -0.1342 0.7469 1.0000
5.000 1.0557 0.01215 0.00822 -0.1266 0.7217 1.0000
5.250 1.0477 0.01248 0.00827 -0.1188 0.6623 1.0000
5.500 1.0224 0.01341 0.00880 -0.1075 0.5972 1.0000
5.750 0.9944 0.01461 0.00965 -0.0961 0.5273 1.0000
6.000 0.9768 0.01571 0.01048 -0.0872 0.4725 1.0000
6.250 0.9604 0.01695 0.01142 -0.0788 0.4195 1.0000
6.500 0.9584 0.01781 0.01210 -0.0734 0.3819 1.0000
6.750 0.9594 0.01863 0.01275 -0.0687 0.3440 1.0000
7.000 0.9573 0.01964 0.01346 -0.0635 0.2846 1.0000
7.250 0.9585 0.02059 0.01417 -0.0590 0.2364 1.0000
7.500 0.9622 0.02149 0.01483 -0.0551 0.1951 1.0000
7.750 0.9700 0.02223 0.01542 -0.0519 0.1677 1.0000
8.000 0.9802 0.02288 0.01596 -0.0492 0.1444 1.0000
8.250 0.9898 0.02358 0.01653 -0.0464 0.1201 1.0000
8.500 1.0013 0.02422 0.01709 -0.0439 0.1036 1.0000
8.750 1.0127 0.02486 0.01767 -0.0415 0.0913 1.0000
9.000 1.0243 0.02552 0.01827 -0.0391 0.0824 1.0000
9.250 1.0379 0.02608 0.01884 -0.0371 0.0759 1.0000
9.500 1.0486 0.02681 0.01953 -0.0346 0.0691 1.0000
9.750 1.0625 0.02736 0.02012 -0.0327 0.0652 1.0000
10.000 1.0737 0.02809 0.02083 -0.0304 0.0603 1.0000
10.250 1.0864 0.02874 0.02153 -0.0284 0.0561 1.0000
10.500 1.0982 0.02946 0.02223 -0.0263 0.0513 1.0000
10.750 1.1105 0.03016 0.02296 -0.0242 0.0477 1.0000
11.000 1.1222 0.03092 0.02375 -0.0221 0.0450 1.0000
11.250 1.1316 0.03183 0.02464 -0.0198 0.0413 1.0000
11.500 1.1447 0.03251 0.02538 -0.0180 0.0389 1.0000
11.750 1.1559 0.03331 0.02620 -0.0161 0.0370 1.0000
12.000 1.1639 0.03438 0.02727 -0.0137 0.0347 1.0000
12.250 1.1745 0.03527 0.02823 -0.0117 0.0336 1.0000
12.500 1.1863 0.03608 0.02909 -0.0099 0.0318 1.0000
12.750 1.1946 0.03717 0.03020 -0.0077 0.0304 1.0000
13.000 1.2000 0.03849 0.03156 -0.0053 0.0289 1.0000
13.250 1.2097 0.03949 0.03264 -0.0034 0.0282 1.0000
13.500 1.2168 0.04073 0.03395 -0.0013 0.0276 1.0000
13.750 1.2281 0.04163 0.03490 0.0002 0.0264 1.0000
14.000 1.2335 0.04305 0.03635 0.0024 0.0253 1.0000
14.250 1.2367 0.04465 0.03799 0.0046 0.0247 1.0000
14.500 1.2390 0.04640 0.03983 0.0070 0.0239 1.0000
14.750 1.2496 0.04743 0.04096 0.0083 0.0233 1.0000
15.000 1.2560 0.04885 0.04247 0.0100 0.0227 1.0000
15.250 1.2594 0.05056 0.04427 0.0120 0.0224 1.0000
15.500 1.2646 0.05214 0.04589 0.0135 0.0216 1.0000
15.750 1.2684 0.05387 0.04769 0.0151 0.0212 1.0000
16.000 1.2702 0.05584 0.04972 0.0168 0.0208 1.0000
16.250 1.2694 0.05808 0.05202 0.0185 0.0200 1.0000
16.500 1.2727 0.05999 0.05406 0.0198 0.0198 1.0000
16.750 1.2736 0.06220 0.05640 0.0212 0.0193 1.0000
17.000 1.2743 0.06448 0.05880 0.0224 0.0190 1.0000
17.250 1.2762 0.06666 0.06108 0.0234 0.0188 1.0000
17.500 1.2744 0.06932 0.06386 0.0245 0.0186 1.0000
17.750 1.2725 0.07207 0.06671 0.0253 0.0182 1.0000
18.000 1.2721 0.07468 0.06941 0.0258 0.0179 1.0000
18.250 1.2682 0.07776 0.07257 0.0263 0.0175 1.0000
18.500 1.2647 0.08083 0.07566 0.0265 0.0169 1.0000
18.750 1.2613 0.08403 0.07909 0.0269 0.0174 1.0000
19.000 1.2552 0.08751 0.08258 0.0269 0.0168 1.0000
19.250 1.2454 0.09155 0.08676 0.0271 0.0166 1.0000
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