K3311 (original) (k3311-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: K3311 (original) (k3311-il) Reynolds number: 200,000 Max Cl/Cd: 77.42 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k3311-il-200000.txt Download as CSV file: xf-k3311-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: K3311 (original)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3947 0.08678 0.08344 -0.0469 1.0000 0.0548
-8.500 -0.4132 0.08319 0.07995 -0.0487 1.0000 0.0549
-8.250 -0.4350 0.07948 0.07626 -0.0505 1.0000 0.0550
-8.000 -0.4536 0.07693 0.07367 -0.0494 1.0000 0.0551
-7.750 -0.4557 0.07217 0.06908 -0.0463 1.0000 0.0563
-7.500 -0.4519 0.07155 0.06855 -0.0413 1.0000 0.0574
-7.250 -0.4600 0.07008 0.06713 -0.0383 1.0000 0.0583
-7.000 -0.4450 0.06626 0.06325 -0.0422 0.9963 0.0609
-6.750 -0.4212 0.05515 0.05145 -0.0600 0.9847 0.0687
-6.500 -0.3931 0.05221 0.04869 -0.0613 0.9806 0.0711
-6.250 -0.3637 0.04763 0.04336 -0.0687 0.9716 0.0822
-6.000 -0.3363 0.04402 0.04005 -0.0701 0.9666 0.0855
-5.750 -0.3063 0.04040 0.03592 -0.0743 0.9590 0.0976
-5.500 -0.2706 0.03738 0.03297 -0.0774 0.9562 0.1028
-5.250 -0.2448 0.03452 0.02982 -0.0790 0.9467 0.1147
-5.000 -0.2085 0.03194 0.02702 -0.0822 0.9431 0.1292
-4.750 -0.1718 0.02304 0.01624 -0.0804 0.9350 0.0575
-4.500 -0.1322 0.02175 0.01463 -0.0819 0.9301 0.0547
-4.250 -0.0962 0.01963 0.01229 -0.0834 0.9249 0.0538
-4.000 -0.0634 0.01865 0.01111 -0.0841 0.9165 0.0548
-3.750 -0.0275 0.01735 0.00968 -0.0853 0.9108 0.0549
-3.500 0.0021 0.01632 0.00857 -0.0854 0.9011 0.0550
-3.250 0.0315 0.01527 0.00751 -0.0854 0.8921 0.0557
-3.000 0.0608 0.01432 0.00655 -0.0855 0.8835 0.0571
-2.750 0.0861 0.01376 0.00598 -0.0848 0.8721 0.0591
-2.500 0.1132 0.01336 0.00554 -0.0845 0.8622 0.0631
-2.250 0.1416 0.01303 0.00510 -0.0842 0.8529 0.0675
-2.000 0.1663 0.01264 0.00469 -0.0834 0.8413 0.0760
-1.750 0.1884 0.01166 0.00430 -0.0825 0.8306 0.2269
-1.500 0.2061 0.01054 0.00429 -0.0806 0.8210 0.5492
-1.250 0.2267 0.01019 0.00430 -0.0787 0.8101 0.6638
-1.000 0.2472 0.00990 0.00433 -0.0764 0.7994 0.7631
-0.750 0.2741 0.00967 0.00426 -0.0753 0.7900 0.8477
-0.500 0.3331 0.00951 0.00412 -0.0810 0.7803 0.9372
-0.250 0.4064 0.00947 0.00393 -0.0902 0.7684 0.9984
0.000 0.4295 0.00952 0.00382 -0.0895 0.7559 1.0000
0.250 0.4522 0.00961 0.00376 -0.0885 0.7446 1.0000
0.500 0.4758 0.00971 0.00372 -0.0877 0.7338 1.0000
0.750 0.4989 0.00982 0.00374 -0.0867 0.7222 1.0000
1.000 0.5228 0.00994 0.00377 -0.0859 0.7114 1.0000
1.250 0.5476 0.01006 0.00378 -0.0852 0.7017 1.0000
1.500 0.5721 0.01020 0.00383 -0.0845 0.6914 1.0000
1.750 0.5965 0.01035 0.00392 -0.0837 0.6811 1.0000
2.000 0.6219 0.01053 0.00400 -0.0832 0.6719 1.0000
2.250 0.6468 0.01070 0.00413 -0.0825 0.6619 1.0000
2.500 0.6712 0.01088 0.00427 -0.0818 0.6514 1.0000
2.750 0.6962 0.01106 0.00439 -0.0812 0.6413 1.0000
3.000 0.7212 0.01121 0.00451 -0.0805 0.6308 1.0000
3.250 0.7454 0.01135 0.00467 -0.0798 0.6201 1.0000
3.500 0.7704 0.01150 0.00480 -0.0791 0.6106 1.0000
3.750 0.7956 0.01164 0.00491 -0.0785 0.6012 1.0000
4.000 0.8200 0.01177 0.00509 -0.0778 0.5905 1.0000
4.250 0.8450 0.01192 0.00525 -0.0772 0.5807 1.0000
4.500 0.8705 0.01209 0.00536 -0.0766 0.5709 1.0000
4.750 0.8944 0.01224 0.00555 -0.0758 0.5586 1.0000
5.000 0.9183 0.01241 0.00574 -0.0750 0.5454 1.0000
5.250 0.9420 0.01260 0.00594 -0.0741 0.5316 1.0000
5.500 0.9653 0.01280 0.00613 -0.0732 0.5168 1.0000
5.750 0.9884 0.01300 0.00637 -0.0722 0.5020 1.0000
6.000 1.0116 0.01324 0.00663 -0.0713 0.4880 1.0000
6.250 1.0348 0.01349 0.00692 -0.0704 0.4740 1.0000
6.500 1.0572 0.01373 0.00720 -0.0693 0.4585 1.0000
6.750 1.0778 0.01396 0.00742 -0.0679 0.4381 1.0000
7.000 1.0963 0.01416 0.00762 -0.0662 0.4100 1.0000
7.250 1.1139 0.01448 0.00787 -0.0643 0.3793 1.0000
7.500 1.1307 0.01492 0.00823 -0.0624 0.3471 1.0000
7.750 1.1465 0.01549 0.00870 -0.0604 0.3148 1.0000
8.000 1.1605 0.01617 0.00928 -0.0582 0.2786 1.0000
8.250 1.1715 0.01703 0.00994 -0.0557 0.2318 1.0000
8.500 1.1756 0.01834 0.01087 -0.0522 0.1670 1.0000
8.750 1.1658 0.02049 0.01238 -0.0469 0.0861 1.0000
9.000 1.1592 0.02233 0.01389 -0.0419 0.0516 1.0000
9.250 1.1623 0.02363 0.01520 -0.0384 0.0438 1.0000
9.500 1.1618 0.02519 0.01680 -0.0348 0.0395 1.0000
9.750 1.1663 0.02652 0.01825 -0.0321 0.0370 1.0000
10.000 1.1696 0.02801 0.01985 -0.0295 0.0354 1.0000
10.250 1.1710 0.02975 0.02165 -0.0271 0.0338 1.0000
10.500 1.1694 0.03188 0.02382 -0.0247 0.0324 1.0000
10.750 1.1703 0.03407 0.02606 -0.0225 0.0313 1.0000
11.000 1.1788 0.03563 0.02774 -0.0210 0.0302 1.0000
11.250 1.1870 0.03729 0.02950 -0.0197 0.0289 1.0000
11.500 1.1956 0.03909 0.03137 -0.0183 0.0277 1.0000
11.750 1.2059 0.04088 0.03324 -0.0171 0.0268 1.0000
12.000 1.2192 0.04267 0.03509 -0.0159 0.0262 1.0000
12.250 1.2353 0.04459 0.03706 -0.0148 0.0256 1.0000
12.500 1.2588 0.04702 0.03959 -0.0140 0.0249 1.0000
12.750 1.2796 0.05083 0.04364 -0.0135 0.0243 1.0000
13.000 1.2774 0.05315 0.04619 -0.0120 0.0241 1.0000
13.250 1.2732 0.05561 0.04889 -0.0108 0.0237 1.0000
13.500 1.2692 0.05862 0.05218 -0.0098 0.0235 1.0000
13.750 1.2631 0.06207 0.05588 -0.0092 0.0233 1.0000
14.000 1.2566 0.06604 0.06010 -0.0088 0.0234 1.0000
14.250 1.2466 0.07034 0.06463 -0.0088 0.0235 1.0000
14.500 1.2334 0.07494 0.06947 -0.0093 0.0235 1.0000
14.750 1.2189 0.07997 0.07473 -0.0103 0.0237 1.0000
15.000 1.2041 0.08548 0.08044 -0.0116 0.0239 1.0000
15.250 1.1849 0.09155 0.08672 -0.0137 0.0240 1.0000
15.500 1.1678 0.09801 0.09336 -0.0161 0.0242 1.0000
15.750 1.1581 0.10357 0.09908 -0.0181 0.0245 1.0000
16.000 1.1436 0.10911 0.10479 -0.0214 0.0247 1.0000
16.250 1.1241 0.11619 0.11207 -0.0260 0.0249 1.0000
16.500 1.0925 0.12663 0.12279 -0.0334 0.0255 1.0000
16.750 0.9680 0.17020 0.16672 -0.0611 0.0331 1.0000
17.000 0.9722 0.17356 0.17010 -0.0626 0.0325 1.0000
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Polar data table (+)
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