GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Reynolds number: 200,000 Max Cl/Cd: 78.24 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe167-il-200000-n5.txt Download as CSV file: xf-goe167-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 167 (V.KARMAN PROP.2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2615 0.10317 0.10001 -0.0242 1.0000 0.0260
-9.500 -0.2583 0.09983 0.09669 -0.0252 1.0000 0.0270
-9.250 -0.3789 0.10688 0.10356 -0.0200 1.0000 0.0233
-9.000 -0.3639 0.10415 0.10083 -0.0171 1.0000 0.0246
-8.750 -0.3570 0.10116 0.09786 -0.0183 1.0000 0.0256
-8.500 -0.3515 0.09791 0.09465 -0.0200 1.0000 0.0263
-8.250 -0.3467 0.09463 0.09141 -0.0218 1.0000 0.0273
-8.000 -0.3450 0.09162 0.08845 -0.0257 1.0000 0.0296
-7.750 -0.3360 0.08739 0.08423 -0.0339 0.9686 0.0302
-7.500 -0.3183 0.08226 0.07905 -0.0419 0.9365 0.0304
-7.250 -0.3012 0.07744 0.07413 -0.0483 0.8979 0.0306
-7.000 -0.2863 0.07288 0.06940 -0.0524 0.8582 0.0307
-6.750 -0.2722 0.06840 0.06471 -0.0553 0.8251 0.0307
-6.500 -0.2566 0.06390 0.05998 -0.0581 0.7976 0.0308
-6.000 -0.2357 0.05657 0.05241 -0.0590 0.7486 0.0330
-5.750 -0.2174 0.05470 0.05037 -0.0597 0.7253 0.0360
-5.500 -0.1775 0.05114 0.04622 -0.0660 0.7064 0.0417
-5.250 -0.1676 0.04672 0.04183 -0.0661 0.6890 0.0383
-5.000 -0.1420 0.04254 0.03733 -0.0685 0.6740 0.0367
-4.750 -0.1137 0.03925 0.03366 -0.0705 0.6602 0.0389
-4.500 -0.0868 0.03574 0.02979 -0.0719 0.6478 0.0374
-4.250 -0.0584 0.03249 0.02614 -0.0731 0.6363 0.0365
-4.000 -0.0296 0.02994 0.02321 -0.0740 0.6259 0.0371
-3.750 -0.0005 0.02776 0.02062 -0.0746 0.6169 0.0381
-3.500 0.0287 0.02556 0.01805 -0.0752 0.6086 0.0376
-3.250 0.0580 0.02369 0.01579 -0.0756 0.6017 0.0375
-3.000 0.0873 0.02212 0.01388 -0.0760 0.5948 0.0376
-2.500 0.1456 0.01998 0.01116 -0.0764 0.5825 0.0394
-2.250 0.1746 0.01903 0.00995 -0.0766 0.5769 0.0396
-2.000 0.2035 0.01818 0.00887 -0.0768 0.5721 0.0395
-1.750 0.2324 0.01744 0.00797 -0.0769 0.5672 0.0397
-1.500 0.2611 0.01683 0.00721 -0.0770 0.5628 0.0399
-1.250 0.2897 0.01632 0.00657 -0.0771 0.5590 0.0403
-1.000 0.3183 0.01587 0.00606 -0.0773 0.5550 0.0408
-0.750 0.3469 0.01549 0.00563 -0.0774 0.5507 0.0412
-0.500 0.3754 0.01521 0.00529 -0.0776 0.5468 0.0418
-0.250 0.4037 0.01476 0.00482 -0.0778 0.5436 0.0440
0.000 0.4323 0.01453 0.00459 -0.0781 0.5403 0.0458
0.250 0.4612 0.01435 0.00441 -0.0784 0.5367 0.0467
0.500 0.4899 0.01423 0.00425 -0.0786 0.5326 0.0479
0.750 0.5185 0.01419 0.00412 -0.0788 0.5287 0.0494
1.000 0.5472 0.01414 0.00404 -0.0790 0.5242 0.0518
1.500 0.6046 0.01404 0.00403 -0.0795 0.5163 0.0810
1.750 0.6263 0.01190 0.00406 -0.0783 0.5134 1.0000
2.000 0.6549 0.01204 0.00412 -0.0785 0.5097 1.0000
2.250 0.6835 0.01217 0.00421 -0.0787 0.5057 1.0000
2.500 0.7120 0.01231 0.00430 -0.0789 0.5022 1.0000
2.750 0.7403 0.01248 0.00440 -0.0791 0.4988 1.0000
3.000 0.7686 0.01261 0.00452 -0.0793 0.4940 1.0000
3.250 0.7967 0.01272 0.00462 -0.0794 0.4875 1.0000
3.500 0.8246 0.01287 0.00471 -0.0795 0.4821 1.0000
3.750 0.8528 0.01297 0.00486 -0.0797 0.4755 1.0000
4.000 0.8807 0.01309 0.00497 -0.0798 0.4693 1.0000
4.250 0.9085 0.01321 0.00513 -0.0799 0.4623 1.0000
4.500 0.9362 0.01332 0.00526 -0.0800 0.4547 1.0000
4.750 0.9640 0.01345 0.00543 -0.0801 0.4477 1.0000
5.000 0.9915 0.01358 0.00561 -0.0802 0.4396 1.0000
5.250 1.0191 0.01372 0.00581 -0.0803 0.4312 1.0000
5.500 1.0462 0.01387 0.00599 -0.0803 0.4223 1.0000
5.750 1.0735 0.01402 0.00623 -0.0804 0.4112 1.0000
6.000 1.1003 0.01419 0.00644 -0.0803 0.3960 1.0000
6.250 1.1266 0.01440 0.00666 -0.0802 0.3755 1.0000
6.500 1.1501 0.01485 0.00690 -0.0798 0.3242 1.0000
6.750 1.1674 0.01611 0.00766 -0.0788 0.2479 1.0000
7.000 1.1881 0.01702 0.00842 -0.0782 0.2179 1.0000
7.250 1.2100 0.01774 0.00909 -0.0777 0.1949 1.0000
7.500 1.2239 0.01928 0.01016 -0.0764 0.1081 1.0000
7.750 1.2382 0.02068 0.01136 -0.0750 0.0760 1.0000
8.000 1.2571 0.02153 0.01224 -0.0740 0.0665 1.0000
8.250 1.2753 0.02239 0.01313 -0.0730 0.0580 1.0000
8.500 1.2947 0.02307 0.01391 -0.0721 0.0510 1.0000
8.750 1.3127 0.02384 0.01475 -0.0709 0.0429 1.0000
9.000 1.3252 0.02500 0.01580 -0.0693 0.0228 1.0000
9.250 1.3340 0.02631 0.01711 -0.0671 0.0191 1.0000
9.500 1.3420 0.02751 0.01841 -0.0647 0.0176 1.0000
9.750 1.3468 0.02881 0.01985 -0.0620 0.0168 1.0000
10.000 1.3504 0.03037 0.02157 -0.0596 0.0161 1.0000
10.250 1.3528 0.03224 0.02358 -0.0577 0.0155 1.0000
10.500 1.3537 0.03446 0.02595 -0.0562 0.0149 1.0000
10.750 1.3532 0.03706 0.02869 -0.0552 0.0143 1.0000
11.000 1.3505 0.04009 0.03186 -0.0546 0.0137 1.0000
11.250 1.3455 0.04357 0.03549 -0.0542 0.0132 1.0000
11.500 1.3406 0.04711 0.03916 -0.0539 0.0128 1.0000
11.750 1.3411 0.05008 0.04226 -0.0537 0.0125 1.0000
12.000 1.3402 0.05321 0.04552 -0.0535 0.0123 1.0000
12.250 1.3388 0.05640 0.04883 -0.0533 0.0121 1.0000
12.500 1.3372 0.05962 0.05217 -0.0531 0.0118 1.0000
12.750 1.3355 0.06282 0.05549 -0.0529 0.0116 1.0000
13.000 1.3339 0.06602 0.05880 -0.0527 0.0114 1.0000
13.250 1.3325 0.06920 0.06208 -0.0525 0.0112 1.0000
13.500 1.3317 0.07233 0.06532 -0.0522 0.0110 1.0000
13.750 1.3313 0.07547 0.06857 -0.0521 0.0108 1.0000
14.000 1.3314 0.07861 0.07182 -0.0520 0.0106 1.0000
14.250 1.3314 0.08180 0.07514 -0.0520 0.0103 1.0000
14.500 1.3311 0.08505 0.07849 -0.0521 0.0100 1.0000
14.750 1.3306 0.08838 0.08191 -0.0523 0.0097 1.0000
15.000 1.3301 0.09169 0.08529 -0.0524 0.0095 1.0000
15.250 1.3300 0.09478 0.08843 -0.0521 0.0092 1.0000
15.500 1.3292 0.09813 0.09189 -0.0520 0.0090 1.0000
15.750 1.3272 0.10205 0.09600 -0.0529 0.0089 1.0000
16.000 1.3246 0.10614 0.10027 -0.0539 0.0088 1.0000
16.250 1.3209 0.11050 0.10482 -0.0552 0.0087 1.0000
16.500 1.3161 0.11515 0.10965 -0.0567 0.0086 1.0000
16.750 1.3102 0.12011 0.11480 -0.0586 0.0085 1.0000
17.000 1.3033 0.12540 0.12029 -0.0608 0.0085 1.0000
17.250 1.2954 0.13108 0.12617 -0.0635 0.0084 1.0000
17.500 1.2865 0.13717 0.13245 -0.0666 0.0084 1.0000
17.750 1.2770 0.14363 0.13910 -0.0702 0.0084 1.0000
18.000 1.2667 0.15051 0.14617 -0.0742 0.0084 1.0000
18.250 1.2556 0.15789 0.15374 -0.0787 0.0084 1.0000
18.500 1.2439 0.16579 0.16182 -0.0838 0.0084 1.0000
18.750 1.2313 0.17442 0.17063 -0.0895 0.0084 1.0000
19.000 1.2179 0.18381 0.18018 -0.0958 0.0085 1.0000
19.250 1.2032 0.19424 0.19076 -0.1028 0.0086 1.0000
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