GRUMMAN K-3 AIRFOIL (k3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GRUMMAN K-3 AIRFOIL (k3-il) Reynolds number: 50,000 Max Cl/Cd: 23.04 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k3-il-50000-n5.txt Download as CSV file: xf-k3-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GRUMMAN K-3 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6054 0.10761 0.09805 -0.0529 0.9999 0.1342
-12.750 -0.7632 0.07952 0.06966 -0.0644 0.9999 0.1386
-12.500 -0.8360 0.06966 0.05952 -0.0657 0.9999 0.1396
-12.250 -0.8818 0.06412 0.05373 -0.0644 0.9999 0.1409
-12.000 -0.8904 0.06199 0.05159 -0.0624 0.9999 0.1431
-11.750 -0.8904 0.06063 0.05027 -0.0603 0.9999 0.1458
-11.500 -0.9081 0.05830 0.04785 -0.0575 0.9999 0.1480
-11.250 -0.9296 0.05575 0.04516 -0.0545 0.9999 0.1501
-11.000 -0.9471 0.05276 0.04188 -0.0527 0.9999 0.1530
-10.750 -0.9345 0.05205 0.04131 -0.0510 0.9999 0.1564
-10.500 -0.9316 0.05050 0.03971 -0.0494 0.9999 0.1604
-10.250 -0.9337 0.04826 0.03719 -0.0482 0.9999 0.1649
-10.000 -0.9199 0.04752 0.03658 -0.0466 0.9999 0.1691
-9.750 -0.9118 0.04611 0.03508 -0.0454 0.9999 0.1744
-9.500 -0.9013 0.04479 0.03369 -0.0444 0.9999 0.1799
-9.250 -0.8880 0.04383 0.03275 -0.0432 0.9999 0.1855
-9.000 -0.8757 0.04247 0.03124 -0.0425 0.9999 0.1924
-8.750 -0.8600 0.04173 0.03059 -0.0414 0.9999 0.1986
-8.500 -0.8450 0.04048 0.02918 -0.0410 0.9999 0.2066
-8.250 -0.8281 0.03981 0.02863 -0.0399 0.9999 0.2136
-8.000 -0.8107 0.03874 0.02745 -0.0397 0.9999 0.2226
-7.750 -0.7928 0.03807 0.02690 -0.0389 0.9999 0.2308
-7.500 -0.7738 0.03717 0.02598 -0.0387 0.9999 0.2411
-7.250 -0.7542 0.03642 0.02528 -0.0385 0.9999 0.2526
-7.000 -0.7340 0.03572 0.02469 -0.0384 0.9999 0.2650
-6.750 -0.7125 0.03501 0.02405 -0.0385 0.9999 0.2791
-6.500 -0.6901 0.03435 0.02346 -0.0388 0.9999 0.2950
-6.250 -0.6674 0.03382 0.02304 -0.0389 0.9999 0.3119
-6.000 -0.6447 0.03346 0.02287 -0.0388 0.9999 0.3299
-5.750 -0.6217 0.03325 0.02281 -0.0386 0.9999 0.3502
-5.500 -0.5994 0.03325 0.02299 -0.0380 0.9999 0.3714
-5.250 -0.5778 0.03348 0.02336 -0.0370 0.9999 0.3922
-5.000 -0.5564 0.03380 0.02378 -0.0359 0.9999 0.4128
-4.750 -0.5345 0.03416 0.02418 -0.0349 0.9999 0.4327
-4.500 -0.5050 0.03472 0.02472 -0.0353 0.9970 0.4530
-4.250 -0.4747 0.03527 0.02524 -0.0360 0.9943 0.4722
-4.000 -0.4441 0.03577 0.02566 -0.0369 0.9918 0.4908
-3.750 -0.4194 0.03651 0.02641 -0.0358 0.9884 0.5034
-3.500 -0.3910 0.03709 0.02696 -0.0359 0.9850 0.5174
-3.250 -0.3580 0.03749 0.02727 -0.0376 0.9822 0.5338
-3.000 -0.3351 0.03825 0.02806 -0.0360 0.9787 0.5432
-2.750 -0.3051 0.03849 0.02824 -0.0371 0.9749 0.5574
-2.500 -0.2800 0.03914 0.02891 -0.0361 0.9711 0.5670
-2.250 -0.2455 0.03949 0.02921 -0.0382 0.9681 0.5803
-2.000 -0.2255 0.03990 0.02966 -0.0363 0.9631 0.5887
-1.750 -0.1917 0.04007 0.02978 -0.0385 0.9589 0.6022
-1.500 -0.1663 0.04068 0.03045 -0.0374 0.9549 0.6100
-1.250 -0.1365 0.04078 0.03052 -0.0388 0.9497 0.6220
-1.000 -0.1109 0.04106 0.03085 -0.0385 0.9445 0.6296
-0.750 -0.0792 0.04144 0.03127 -0.0393 0.9401 0.6379
-0.500 -0.0462 0.04139 0.03119 -0.0419 0.9339 0.6483
-0.250 -0.0201 0.04163 0.03150 -0.0414 0.9279 0.6536
0.000 0.0101 0.04182 0.03174 -0.0422 0.9221 0.6602
0.250 0.0434 0.04186 0.03180 -0.0445 0.9148 0.6680
0.500 0.0822 0.04203 0.03202 -0.0471 0.9095 0.6740
0.750 0.1041 0.04206 0.03214 -0.0463 0.9001 0.6790
1.000 0.1429 0.04219 0.03234 -0.0488 0.8936 0.6850
1.250 0.1749 0.04219 0.03240 -0.0507 0.8835 0.6914
1.500 0.2166 0.04219 0.03249 -0.0535 0.8760 0.6965
1.750 0.2419 0.04208 0.03250 -0.0530 0.8633 0.7010
2.000 0.2782 0.04180 0.03233 -0.0545 0.8504 0.7062
2.250 0.3238 0.04101 0.03164 -0.0571 0.8328 0.7120
2.500 0.3667 0.03988 0.03061 -0.0586 0.8110 0.7174
2.750 0.4007 0.03877 0.02964 -0.0580 0.7897 0.7217
3.000 0.4342 0.03783 0.02884 -0.0579 0.7692 0.7265
3.250 0.4678 0.03696 0.02811 -0.0580 0.7474 0.7318
3.500 0.5040 0.03605 0.02734 -0.0587 0.7232 0.7376
3.750 0.5202 0.03569 0.02715 -0.0559 0.6923 0.7417
4.000 0.5405 0.03522 0.02684 -0.0539 0.6543 0.7463
4.250 0.5767 0.03389 0.02558 -0.0532 0.6028 0.7515
4.500 0.6470 0.03120 0.02216 -0.0555 0.4818 0.7578
4.750 0.6678 0.03174 0.02201 -0.0534 0.3882 0.7622
5.250 0.6992 0.03380 0.02333 -0.0500 0.2933 0.7720
5.500 0.7222 0.03480 0.02407 -0.0499 0.2656 0.7773
5.750 0.7450 0.03561 0.02475 -0.0493 0.2447 0.7822
6.000 0.7680 0.03632 0.02539 -0.0485 0.2278 0.7876
6.250 0.7959 0.03702 0.02608 -0.0486 0.2122 0.7938
6.500 0.8282 0.03778 0.02681 -0.0496 0.1979 0.8001
6.750 0.8559 0.03842 0.02742 -0.0493 0.1861 0.8057
7.000 0.8853 0.03917 0.02814 -0.0496 0.1744 0.8119
7.250 0.9160 0.04007 0.02913 -0.0503 0.1626 0.8188
7.500 0.9396 0.04090 0.02999 -0.0496 0.1528 0.8254
7.750 0.9635 0.04182 0.03084 -0.0492 0.1436 0.8331
8.000 0.9845 0.04287 0.03209 -0.0485 0.1339 0.8408
8.250 1.0041 0.04392 0.03323 -0.0474 0.1258 0.8488
8.500 1.0252 0.04501 0.03425 -0.0469 0.1187 0.8575
8.750 1.0396 0.04623 0.03576 -0.0450 0.1113 0.8666
9.000 1.0555 0.04749 0.03713 -0.0437 0.1052 0.8772
9.250 1.0690 0.04870 0.03844 -0.0420 0.0998 0.8895
9.500 1.0795 0.05015 0.04012 -0.0398 0.0946 0.9035
9.750 1.0900 0.05135 0.04141 -0.0379 0.0906 0.9213
10.000 1.0979 0.05309 0.04342 -0.0358 0.0864 0.9476
10.250 1.1074 0.05464 0.04512 -0.0347 0.0829 1.0001
10.500 1.1200 0.05720 0.04790 -0.0345 0.0794 1.0001
10.750 1.1283 0.05990 0.05084 -0.0340 0.0762 1.0001
11.000 1.1416 0.06187 0.05277 -0.0339 0.0739 1.0001
11.250 1.1336 0.06597 0.05735 -0.0325 0.0716 1.0001
11.500 1.1297 0.06951 0.06116 -0.0316 0.0697 1.0001
11.750 1.1299 0.07262 0.06440 -0.0312 0.0683 1.0001
12.000 1.1293 0.07589 0.06775 -0.0309 0.0671 1.0001
12.250 1.1020 0.08200 0.07430 -0.0307 0.0665 1.0001
12.500 1.0699 0.08910 0.08180 -0.0319 0.0662 1.0001
12.750 1.0299 0.09806 0.09113 -0.0353 0.0662 1.0001
13.000 0.9794 0.11053 0.10394 -0.0425 0.0666 1.0001
13.250 0.9075 0.13210 0.12584 -0.0576 0.0671 1.0001
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