GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GRUMMAN K-2 AIRFOIL (k2-il) Reynolds number: 200,000 Max Cl/Cd: 35.06 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k2-il-200000-n5.txt Download as CSV file: xf-k2-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GRUMMAN K-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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.8299 0.06246 0.05741 -0.0515 1.0000 0.0185
-10.750 -0.8516 0.05800 0.05278 -0.0517 1.0000 0.0185
-10.500 -0.8729 0.05418 0.04876 -0.0505 1.0000 0.0185
-10.250 -0.8929 0.05100 0.04539 -0.0480 1.0000 0.0185
-10.000 -0.9131 0.04838 0.04258 -0.0443 1.0000 0.0185
-9.750 -0.9308 0.04598 0.03997 -0.0402 1.0000 0.0185
-9.500 -0.9378 0.04343 0.03722 -0.0376 1.0000 0.0186
-9.250 -0.9384 0.04123 0.03482 -0.0352 1.0000 0.0186
-9.000 -0.9348 0.03920 0.03261 -0.0331 1.0000 0.0188
-8.750 -0.9275 0.03740 0.03064 -0.0313 1.0000 0.0189
-8.500 -0.9172 0.03586 0.02896 -0.0297 1.0000 0.0192
-8.250 -0.9049 0.03443 0.02737 -0.0282 1.0000 0.0195
-8.000 -0.8910 0.03301 0.02579 -0.0269 1.0000 0.0199
-7.750 -0.8760 0.03149 0.02406 -0.0256 1.0000 0.0204
-7.500 -0.8597 0.02987 0.02220 -0.0244 1.0000 0.0209
-7.250 -0.8420 0.02826 0.02033 -0.0232 1.0000 0.0214
-7.000 -0.8229 0.02678 0.01861 -0.0221 1.0000 0.0217
-6.750 -0.8029 0.02548 0.01709 -0.0210 1.0000 0.0221
-6.500 -0.7826 0.02435 0.01593 -0.0201 1.0000 0.0225
-6.250 -0.7616 0.02344 0.01499 -0.0193 1.0000 0.0229
-6.000 -0.7401 0.02260 0.01410 -0.0186 1.0000 0.0235
-5.750 -0.7181 0.02178 0.01322 -0.0179 1.0000 0.0242
-5.500 -0.6955 0.02097 0.01235 -0.0172 1.0000 0.0250
-5.250 -0.6723 0.02022 0.01151 -0.0167 1.0000 0.0260
-5.000 -0.6487 0.01953 0.01084 -0.0164 1.0000 0.0271
-4.750 -0.6244 0.01898 0.01030 -0.0162 1.0000 0.0287
-4.500 -0.5994 0.01841 0.00967 -0.0160 1.0000 0.0305
-4.250 -0.5738 0.01775 0.00904 -0.0161 1.0000 0.0320
-4.000 -0.5475 0.01721 0.00850 -0.0163 1.0000 0.0340
-3.750 -0.5206 0.01672 0.00799 -0.0166 1.0000 0.0368
-3.500 -0.4934 0.01628 0.00758 -0.0169 1.0000 0.0405
-3.250 -0.4653 0.01582 0.00712 -0.0174 1.0000 0.0448
-3.000 -0.4370 0.01542 0.00675 -0.0179 1.0000 0.0510
-2.750 -0.4080 0.01501 0.00640 -0.0186 1.0000 0.0610
-2.500 -0.3779 0.01454 0.00607 -0.0196 1.0000 0.0822
-2.250 -0.3432 0.01370 0.00570 -0.0220 1.0000 0.1681
-2.000 -0.2987 0.01239 0.00529 -0.0272 1.0000 0.3573
-1.750 -0.2555 0.01131 0.00542 -0.0312 1.0000 0.5955
-1.500 -0.2363 0.01155 0.00594 -0.0288 1.0000 0.6669
-1.250 -0.2170 0.01194 0.00643 -0.0264 1.0000 0.7069
-1.000 -0.1905 0.01255 0.00708 -0.0253 0.9970 0.7393
-0.750 -0.1604 0.01302 0.00754 -0.0253 0.9945 0.7544
-0.500 -0.1306 0.01328 0.00778 -0.0254 0.9912 0.7606
-0.250 -0.0946 0.01342 0.00787 -0.0271 0.9880 0.7688
0.000 -0.0646 0.01382 0.00830 -0.0269 0.9842 0.7741
0.250 -0.0321 0.01400 0.00847 -0.0276 0.9786 0.7823
0.500 0.0104 0.01405 0.00853 -0.0304 0.9723 0.7866
0.750 0.0487 0.01391 0.00840 -0.0320 0.9609 0.7886
1.000 0.0845 0.01371 0.00823 -0.0331 0.9494 0.7908
1.250 0.1241 0.01336 0.00790 -0.0349 0.9341 0.7930
1.500 0.1614 0.01292 0.00749 -0.0361 0.9145 0.7955
1.750 0.1914 0.01269 0.00730 -0.0363 0.8964 0.7991
2.000 0.2266 0.01242 0.00705 -0.0376 0.8740 0.8024
2.250 0.2867 0.01197 0.00655 -0.0433 0.8160 0.8029
2.500 0.3392 0.01261 0.00615 -0.0472 0.5797 0.8034
2.750 0.3545 0.01341 0.00639 -0.0445 0.4492 0.8053
3.000 0.3737 0.01408 0.00661 -0.0428 0.3450 0.8073
3.250 0.3964 0.01459 0.00682 -0.0419 0.2748 0.8097
3.500 0.4208 0.01510 0.00704 -0.0415 0.2117 0.8123
3.750 0.4475 0.01553 0.00725 -0.0416 0.1660 0.8150
4.000 0.4766 0.01590 0.00746 -0.0422 0.1340 0.8179
4.250 0.5030 0.01626 0.00770 -0.0421 0.1092 0.8200
4.500 0.5270 0.01660 0.00796 -0.0413 0.0892 0.8215
4.750 0.5520 0.01694 0.00823 -0.0408 0.0693 0.8231
5.000 0.5770 0.01740 0.00856 -0.0403 0.0453 0.8249
5.250 0.6017 0.01799 0.00904 -0.0398 0.0330 0.8270
5.500 0.6275 0.01857 0.00962 -0.0395 0.0278 0.8294
5.750 0.6545 0.01915 0.01024 -0.0394 0.0248 0.8317
6.000 0.6819 0.01980 0.01091 -0.0396 0.0229 0.8338
6.250 0.7095 0.02038 0.01158 -0.0398 0.0211 0.8359
6.500 0.7324 0.02095 0.01217 -0.0388 0.0197 0.8374
6.750 0.7556 0.02157 0.01288 -0.0380 0.0184 0.8390
7.000 0.7794 0.02223 0.01363 -0.0373 0.0174 0.8407
7.250 0.8032 0.02298 0.01444 -0.0367 0.0167 0.8424
7.500 0.8270 0.02384 0.01533 -0.0362 0.0162 0.8441
7.750 0.8509 0.02485 0.01645 -0.0357 0.0158 0.8462
8.000 0.8755 0.02596 0.01772 -0.0353 0.0154 0.8484
8.250 0.9005 0.02722 0.01915 -0.0351 0.0150 0.8506
8.500 0.9229 0.02851 0.02064 -0.0344 0.0147 0.8521
8.750 0.9430 0.02988 0.02221 -0.0332 0.0144 0.8534
9.000 0.9622 0.03138 0.02394 -0.0319 0.0142 0.8548
9.250 0.9803 0.03302 0.02583 -0.0306 0.0140 0.8564
9.500 0.9969 0.03486 0.02796 -0.0292 0.0139 0.8584
9.750 1.0117 0.03690 0.03029 -0.0277 0.0138 0.8605
10.000 1.0242 0.03923 0.03295 -0.0261 0.0137 0.8626
10.250 1.0333 0.04195 0.03603 -0.0244 0.0136 0.8645
10.500 1.0376 0.04512 0.03960 -0.0224 0.0136 0.8664
10.750 1.0322 0.04866 0.04356 -0.0193 0.0136 0.8679
11.000 1.0108 0.05316 0.04855 -0.0150 0.0137 0.8698
11.250 0.9743 0.05937 0.05525 -0.0116 0.0139 0.8723
11.500 0.9162 0.07040 0.06681 -0.0143 0.0142 0.8748
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Polar data table (+)
Polar graphs
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