K3311 (original) (k3311-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: K3311 (original) (k3311-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.54 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k3311-il-1000000.txt Download as CSV file: xf-k3311-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4330 0.04308 0.04118 -0.0791 0.9807 0.0148
-8.000 -0.4378 0.02726 0.02426 -0.0859 0.9699 0.0154
-7.750 -0.4197 0.02323 0.01973 -0.0870 0.9597 0.0165
-7.500 -0.3872 0.02323 0.01980 -0.0886 0.9535 0.0170
-7.250 -0.3544 0.02397 0.02065 -0.0899 0.9447 0.0179
-7.000 -0.3323 0.02154 0.01788 -0.0899 0.9313 0.0185
-6.750 -0.3111 0.01942 0.01542 -0.0892 0.9175 0.0189
-6.500 -0.2883 0.01811 0.01384 -0.0885 0.9043 0.0196
-6.250 -0.2641 0.01790 0.01332 -0.0877 0.8915 0.0208
-6.000 -0.2437 0.01561 0.01081 -0.0869 0.8790 0.0215
-5.750 -0.2193 0.01507 0.01024 -0.0865 0.8667 0.0224
-5.500 -0.1955 0.01399 0.00897 -0.0857 0.8539 0.0224
-5.250 -0.1709 0.01324 0.00810 -0.0851 0.8407 0.0228
-5.000 -0.1461 0.01250 0.00723 -0.0844 0.8272 0.0231
-4.750 -0.1210 0.01198 0.00662 -0.0838 0.8130 0.0238
-4.500 -0.0958 0.01155 0.00609 -0.0833 0.7985 0.0245
-4.250 -0.0708 0.01101 0.00544 -0.0826 0.7847 0.0248
-4.000 -0.0457 0.01057 0.00490 -0.0820 0.7717 0.0251
-3.750 -0.0206 0.01016 0.00440 -0.0814 0.7597 0.0253
-3.250 0.0303 0.00944 0.00354 -0.0803 0.7376 0.0257
-3.000 0.0564 0.00922 0.00326 -0.0799 0.7271 0.0261
-2.750 0.0827 0.00907 0.00306 -0.0795 0.7165 0.0265
-2.500 0.1079 0.00870 0.00261 -0.0790 0.7060 0.0269
-2.250 0.1332 0.00833 0.00215 -0.0784 0.6957 0.0278
-2.000 0.1592 0.00816 0.00190 -0.0779 0.6852 0.0285
-1.750 0.1854 0.00805 0.00172 -0.0776 0.6755 0.0293
-1.500 0.2123 0.00794 0.00157 -0.0773 0.6673 0.0302
-1.000 0.2664 0.00780 0.00135 -0.0768 0.6527 0.0327
-0.750 0.2934 0.00777 0.00127 -0.0766 0.6457 0.0347
-0.500 0.3203 0.00757 0.00119 -0.0764 0.6387 0.0734
-0.250 0.3424 0.00677 0.00111 -0.0757 0.6309 0.3285
0.000 0.3656 0.00622 0.00112 -0.0750 0.6223 0.5195
0.250 0.3914 0.00610 0.00114 -0.0745 0.6130 0.5793
0.500 0.4172 0.00599 0.00115 -0.0741 0.6025 0.6307
0.750 0.4422 0.00586 0.00118 -0.0735 0.5909 0.6923
1.000 0.4659 0.00574 0.00122 -0.0725 0.5775 0.7625
1.250 0.4875 0.00556 0.00127 -0.0710 0.5647 0.8512
1.500 0.5532 0.00547 0.00136 -0.0793 0.5504 0.9716
1.750 0.6030 0.00560 0.00141 -0.0843 0.5394 1.0000
2.000 0.6279 0.00569 0.00146 -0.0837 0.5305 1.0000
2.250 0.6529 0.00578 0.00151 -0.0831 0.5228 1.0000
2.500 0.6778 0.00588 0.00157 -0.0824 0.5143 1.0000
2.750 0.7030 0.00598 0.00164 -0.0819 0.5051 1.0000
3.000 0.7278 0.00610 0.00172 -0.0812 0.4957 1.0000
3.250 0.7533 0.00619 0.00179 -0.0807 0.4875 1.0000
3.500 0.7783 0.00631 0.00188 -0.0802 0.4784 1.0000
4.000 0.8286 0.00655 0.00207 -0.0791 0.4584 1.0000
4.250 0.8536 0.00668 0.00217 -0.0785 0.4483 1.0000
4.500 0.8784 0.00682 0.00228 -0.0779 0.4361 1.0000
5.000 0.9275 0.00716 0.00253 -0.0766 0.4018 1.0000
5.250 0.9508 0.00741 0.00269 -0.0758 0.3791 1.0000
5.500 0.9737 0.00770 0.00287 -0.0749 0.3531 1.0000
5.750 0.9956 0.00805 0.00311 -0.0739 0.3247 1.0000
6.000 1.0171 0.00845 0.00337 -0.0728 0.2946 1.0000
6.250 1.0388 0.00884 0.00363 -0.0718 0.2657 1.0000
6.500 1.0588 0.00935 0.00395 -0.0705 0.2287 1.0000
6.750 1.0783 0.00989 0.00433 -0.0692 0.1946 1.0000
7.000 1.0957 0.01057 0.00477 -0.0675 0.1510 1.0000
7.250 1.1113 0.01137 0.00532 -0.0655 0.1071 1.0000
7.500 1.1282 0.01206 0.00584 -0.0638 0.0766 1.0000
7.750 1.1376 0.01325 0.00669 -0.0608 0.0270 1.0000
8.000 1.1547 0.01388 0.00729 -0.0590 0.0186 1.0000
8.250 1.1747 0.01429 0.00773 -0.0578 0.0168 1.0000
8.500 1.1921 0.01484 0.00830 -0.0561 0.0148 1.0000
8.750 1.2094 0.01538 0.00889 -0.0544 0.0139 1.0000
9.000 1.2273 0.01584 0.00940 -0.0528 0.0131 1.0000
9.250 1.2427 0.01633 0.00993 -0.0508 0.0125 1.0000
9.500 1.2555 0.01687 0.01052 -0.0483 0.0119 1.0000
9.750 1.2652 0.01759 0.01128 -0.0454 0.0112 1.0000
10.000 1.2703 0.01857 0.01236 -0.0419 0.0106 1.0000
10.250 1.2827 0.01921 0.01305 -0.0397 0.0104 1.0000
10.500 1.2962 0.01981 0.01370 -0.0378 0.0100 1.0000
10.750 1.3065 0.02062 0.01458 -0.0356 0.0097 1.0000
11.000 1.3164 0.02149 0.01551 -0.0335 0.0094 1.0000
11.250 1.3259 0.02243 0.01651 -0.0315 0.0091 1.0000
11.500 1.3332 0.02356 0.01770 -0.0294 0.0088 1.0000
11.750 1.3403 0.02478 0.01897 -0.0276 0.0084 1.0000
12.000 1.3443 0.02630 0.02057 -0.0256 0.0084 1.0000
12.250 1.3445 0.02821 0.02257 -0.0237 0.0081 1.0000
12.500 1.3348 0.03111 0.02561 -0.0214 0.0078 1.0000
12.750 1.3354 0.03330 0.02789 -0.0201 0.0077 1.0000
13.000 1.3407 0.03514 0.02982 -0.0193 0.0076 1.0000
13.250 1.3463 0.03701 0.03177 -0.0186 0.0076 1.0000
13.500 1.3503 0.03911 0.03396 -0.0179 0.0074 1.0000
13.750 1.3564 0.04107 0.03600 -0.0176 0.0072 1.0000
14.000 1.3548 0.04382 0.03885 -0.0170 0.0072 1.0000
14.250 1.3571 0.04625 0.04137 -0.0167 0.0070 1.0000
14.500 1.3605 0.04864 0.04383 -0.0167 0.0068 1.0000
14.750 1.3587 0.05163 0.04693 -0.0165 0.0067 1.0000
15.000 1.3550 0.05490 0.05030 -0.0164 0.0068 1.0000
15.250 1.3577 0.05765 0.05313 -0.0169 0.0065 1.0000
15.500 1.3587 0.06065 0.05620 -0.0175 0.0063 1.0000
15.750 1.3557 0.06415 0.05979 -0.0181 0.0062 1.0000
16.000 1.3505 0.06798 0.06374 -0.0186 0.0062 1.0000
16.250 1.3493 0.07153 0.06735 -0.0196 0.0061 1.0000
16.500 1.3444 0.07554 0.07146 -0.0206 0.0060 1.0000
16.750 1.3378 0.07983 0.07587 -0.0217 0.0060 1.0000
17.000 1.3308 0.08438 0.08047 -0.0231 0.0058 1.0000
17.250 1.3251 0.08882 0.08501 -0.0246 0.0058 1.0000
17.500 1.3159 0.09379 0.09010 -0.0262 0.0057 1.0000
17.750 1.3060 0.09902 0.09544 -0.0281 0.0057 1.0000
18.000 1.2958 0.10447 0.10101 -0.0302 0.0056 1.0000
18.250 1.2752 0.11169 0.10841 -0.0329 0.0055 1.0000
18.500 1.2686 0.11697 0.11379 -0.0355 0.0056 1.0000
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Polar data table (+)
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