GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Reynolds number: 200,000 Max Cl/Cd: 80.78 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe167-il-200000.txt Download as CSV file: xf-goe167-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3776 0.10842 0.10511 -0.0209 1.0000 0.0354
-8.750 -0.3763 0.10538 0.10212 -0.0247 1.0000 0.0355
-8.500 -0.3753 0.10208 0.09886 -0.0288 1.0000 0.0356
-8.250 -0.3675 0.09595 0.09276 -0.0260 1.0000 0.0362
-8.000 -0.3558 0.09233 0.08914 -0.0243 1.0000 0.0370
-7.750 -0.3494 0.08924 0.08609 -0.0247 1.0000 0.0377
-7.500 -0.3439 0.08615 0.08304 -0.0261 1.0000 0.0386
-7.250 -0.3368 0.08283 0.07976 -0.0287 1.0000 0.0396
-7.000 -0.3293 0.07945 0.07643 -0.0319 1.0000 0.0412
-6.750 -0.3228 0.07612 0.07313 -0.0357 1.0000 0.0432
-6.500 -0.2797 0.07078 0.06746 -0.0548 0.9895 0.0454
-6.250 -0.2610 0.06344 0.06019 -0.0579 0.9770 0.0466
-6.000 -0.2354 0.05980 0.05656 -0.0601 0.9587 0.0480
-5.750 -0.2097 0.05631 0.05297 -0.0633 0.9294 0.0502
-5.500 -0.1864 0.05288 0.04934 -0.0660 0.8897 0.0537
-5.250 -0.1556 0.04819 0.04402 -0.0712 0.8531 0.0585
-5.000 -0.1420 0.04541 0.04115 -0.0699 0.8172 0.0598
-4.750 -0.1233 0.04324 0.03877 -0.0697 0.7871 0.0620
-4.500 -0.0867 0.04321 0.03789 -0.0716 0.7624 0.0706
-4.250 -0.0680 0.03786 0.03248 -0.0727 0.7432 0.0725
-4.000 -0.0464 0.03575 0.03032 -0.0730 0.7249 0.0755
-3.750 -0.0142 0.03440 0.02832 -0.0742 0.7100 0.0859
-3.500 0.0089 0.03170 0.02562 -0.0747 0.6973 0.0886
-3.250 0.0402 0.03103 0.02437 -0.0753 0.6862 0.1000
-3.000 0.0648 0.02828 0.02168 -0.0761 0.6760 0.1036
-2.750 0.0940 0.02699 0.02003 -0.0767 0.6677 0.1159
-2.500 0.1219 0.02566 0.01852 -0.0774 0.6592 0.1305
-2.250 0.1492 0.02429 0.01702 -0.0780 0.6520 0.1465
-2.000 0.1768 0.02303 0.01569 -0.0785 0.6446 0.1644
-1.750 0.2049 0.02209 0.01453 -0.0790 0.6388 0.1915
-1.500 0.2511 0.01971 0.01088 -0.0769 0.6333 0.0714
-1.250 0.2803 0.01875 0.00978 -0.0770 0.6279 0.0699
-1.000 0.3094 0.01802 0.00888 -0.0771 0.6233 0.0699
-0.750 0.3386 0.01711 0.00791 -0.0772 0.6179 0.0687
-0.500 0.3675 0.01649 0.00720 -0.0773 0.6130 0.0681
-0.250 0.3961 0.01605 0.00668 -0.0773 0.6089 0.0683
0.000 0.4250 0.01565 0.00631 -0.0775 0.6042 0.0692
0.250 0.4538 0.01538 0.00603 -0.0777 0.5999 0.0705
0.500 0.4824 0.01505 0.00572 -0.0779 0.5959 0.0753
0.750 0.5113 0.01496 0.00564 -0.0782 0.5913 0.0815
1.000 0.5404 0.01482 0.00551 -0.0784 0.5860 0.0902
1.250 0.5625 0.01239 0.00536 -0.0772 0.5816 1.0000
1.500 0.5913 0.01261 0.00533 -0.0773 0.5772 1.0000
1.750 0.6201 0.01278 0.00544 -0.0775 0.5726 1.0000
2.000 0.6488 0.01299 0.00557 -0.0778 0.5689 1.0000
2.250 0.6773 0.01323 0.00569 -0.0780 0.5655 1.0000
2.500 0.7058 0.01345 0.00589 -0.0782 0.5613 1.0000
2.750 0.7342 0.01363 0.00608 -0.0784 0.5562 1.0000
3.000 0.7626 0.01384 0.00623 -0.0786 0.5521 1.0000
3.250 0.7908 0.01407 0.00640 -0.0787 0.5473 1.0000
3.500 0.8187 0.01419 0.00658 -0.0789 0.5407 1.0000
3.750 0.8467 0.01434 0.00664 -0.0789 0.5349 1.0000
4.000 0.8744 0.01448 0.00683 -0.0790 0.5278 1.0000
4.250 0.9023 0.01458 0.00690 -0.0790 0.5212 1.0000
4.500 0.9300 0.01474 0.00709 -0.0790 0.5150 1.0000
4.750 0.9577 0.01488 0.00730 -0.0791 0.5092 1.0000
5.000 0.9856 0.01504 0.00742 -0.0791 0.5040 1.0000
5.250 1.0129 0.01516 0.00768 -0.0792 0.4968 1.0000
5.500 1.0404 0.01524 0.00775 -0.0791 0.4900 1.0000
5.750 1.0674 0.01530 0.00792 -0.0791 0.4813 1.0000
6.000 1.0947 0.01533 0.00795 -0.0790 0.4735 1.0000
6.250 1.1215 0.01539 0.00818 -0.0789 0.4644 1.0000
6.500 1.1481 0.01538 0.00824 -0.0787 0.4537 1.0000
6.750 1.1743 0.01531 0.00824 -0.0784 0.4393 1.0000
7.000 1.2002 0.01526 0.00830 -0.0781 0.4205 1.0000
7.250 1.2256 0.01530 0.00838 -0.0777 0.3978 1.0000
7.500 1.2505 0.01548 0.00858 -0.0774 0.3689 1.0000
7.750 1.2722 0.01596 0.00887 -0.0766 0.3162 1.0000
8.000 1.2876 0.01723 0.00972 -0.0753 0.2529 1.0000
8.250 1.3044 0.01841 0.01072 -0.0742 0.2171 1.0000
8.500 1.3212 0.01954 0.01171 -0.0730 0.1734 1.0000
8.750 1.3222 0.02208 0.01357 -0.0702 0.0870 1.0000
9.000 1.3310 0.02372 0.01517 -0.0680 0.0708 1.0000
9.250 1.3378 0.02534 0.01684 -0.0655 0.0575 1.0000
9.500 1.3404 0.02707 0.01867 -0.0625 0.0466 1.0000
9.750 1.3456 0.02834 0.02005 -0.0597 0.0401 1.0000
10.000 1.3415 0.03041 0.02214 -0.0565 0.0369 1.0000
10.250 1.3449 0.03221 0.02409 -0.0546 0.0344 1.0000
10.500 1.3483 0.03421 0.02618 -0.0532 0.0321 1.0000
10.750 1.3496 0.03661 0.02863 -0.0522 0.0302 1.0000
11.000 1.3454 0.03975 0.03184 -0.0514 0.0290 1.0000
11.250 1.3460 0.04252 0.03474 -0.0507 0.0281 1.0000
11.500 1.3461 0.04538 0.03773 -0.0500 0.0273 1.0000
11.750 1.3464 0.04820 0.04064 -0.0494 0.0266 1.0000
12.000 1.3475 0.05092 0.04345 -0.0486 0.0259 1.0000
12.250 1.3493 0.05353 0.04613 -0.0478 0.0253 1.0000
12.500 1.3520 0.05601 0.04868 -0.0468 0.0248 1.0000
12.750 1.3557 0.05835 0.05108 -0.0456 0.0243 1.0000
13.000 1.3605 0.06053 0.05329 -0.0441 0.0237 1.0000
13.250 1.3698 0.06229 0.05510 -0.0414 0.0230 1.0000
13.500 1.3752 0.06474 0.05775 -0.0406 0.0225 1.0000
13.750 1.3804 0.06728 0.06047 -0.0397 0.0221 1.0000
14.000 1.3859 0.06995 0.06334 -0.0385 0.0218 1.0000
14.250 1.3893 0.07305 0.06665 -0.0375 0.0217 1.0000
14.500 1.3888 0.07669 0.07054 -0.0369 0.0217 1.0000
14.750 1.3843 0.08087 0.07496 -0.0367 0.0217 1.0000
15.000 1.3762 0.08556 0.07991 -0.0370 0.0218 1.0000
15.250 1.3652 0.09071 0.08530 -0.0378 0.0219 1.0000
15.500 1.3520 0.09624 0.09107 -0.0390 0.0220 1.0000
15.750 1.3371 0.10218 0.09724 -0.0408 0.0222 1.0000
16.000 1.3213 0.10848 0.10374 -0.0431 0.0224 1.0000
16.250 1.3048 0.11509 0.11055 -0.0459 0.0225 1.0000
16.500 1.2879 0.12205 0.11769 -0.0491 0.0227 1.0000
16.750 1.2721 0.12919 0.12499 -0.0524 0.0229 1.0000
17.000 1.2600 0.13583 0.13180 -0.0562 0.0232 1.0000
17.250 1.2405 0.14469 0.14091 -0.0625 0.0236 1.0000
17.500 1.1028 0.20007 0.19675 -0.0988 0.0313 1.0000
17.750 1.1153 0.19919 0.19590 -0.0982 0.0302 1.0000
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Polar data table (+)
Polar graphs
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