GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GRUMMAN K-2 AIRFOIL (k2-il) Reynolds number: 200,000 Max Cl/Cd: 28.99 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k2-il-200000.txt Download as CSV file: xf-k2-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4772 0.11361 0.10970 -0.0240 1.0000 0.0645
-10.250 -0.5118 0.10494 0.10107 -0.0309 1.0000 0.0675
-10.000 -0.5647 0.09247 0.08859 -0.0409 1.0000 0.0678
-9.750 -0.5345 0.09248 0.08867 -0.0345 1.0000 0.0690
-9.500 -0.5214 0.09139 0.08759 -0.0318 1.0000 0.0700
-9.250 -0.5194 0.08830 0.08452 -0.0312 1.0000 0.0712
-9.000 -0.5264 0.08356 0.07980 -0.0322 1.0000 0.0726
-8.750 -0.5465 0.07616 0.07243 -0.0356 1.0000 0.0736
-8.500 -0.5893 0.06668 0.06291 -0.0405 1.0000 0.0735
-8.250 -0.6288 0.06076 0.05692 -0.0408 1.0000 0.0732
-8.000 -0.7956 0.06448 0.05996 -0.0339 1.0000 0.0693
-7.750 -0.7867 0.06176 0.05728 -0.0327 1.0000 0.0703
-7.500 -0.7827 0.05923 0.05472 -0.0311 1.0000 0.0715
-7.250 -0.7808 0.05659 0.05198 -0.0296 1.0000 0.0734
-6.750 -0.7995 0.03800 0.03098 -0.0241 1.0000 0.0426
-6.500 -0.7807 0.03550 0.02830 -0.0232 1.0000 0.0421
-6.250 -0.7616 0.03277 0.02532 -0.0225 1.0000 0.0419
-6.000 -0.7409 0.03027 0.02258 -0.0218 1.0000 0.0416
-5.750 -0.7188 0.02798 0.02007 -0.0211 1.0000 0.0412
-5.500 -0.6956 0.02606 0.01792 -0.0203 1.0000 0.0411
-5.250 -0.6717 0.02448 0.01613 -0.0195 1.0000 0.0413
-5.000 -0.6474 0.02322 0.01466 -0.0188 1.0000 0.0419
-4.750 -0.6233 0.02188 0.01322 -0.0180 1.0000 0.0428
-4.500 -0.5996 0.02067 0.01209 -0.0174 1.0000 0.0443
-4.250 -0.5749 0.01997 0.01139 -0.0169 1.0000 0.0471
-4.000 -0.5495 0.01940 0.01071 -0.0165 1.0000 0.0496
-3.750 -0.5247 0.01815 0.00963 -0.0162 1.0000 0.0526
-3.500 -0.4984 0.01746 0.00896 -0.0161 1.0000 0.0564
-3.250 -0.4706 0.01661 0.00818 -0.0167 1.0000 0.0624
-3.000 -0.4412 0.01585 0.00748 -0.0175 1.0000 0.0705
-2.750 -0.4099 0.01508 0.00682 -0.0188 1.0000 0.0856
-2.500 -0.3417 0.01126 0.00579 -0.0306 1.0000 0.5904
-2.250 -0.3281 0.01174 0.00662 -0.0263 1.0000 0.6869
-2.000 -0.3096 0.01228 0.00717 -0.0235 1.0000 0.7215
-1.750 -0.2930 0.01290 0.00778 -0.0202 1.0000 0.7417
-1.500 -0.2770 0.01352 0.00837 -0.0168 1.0000 0.7568
-1.250 -0.2611 0.01413 0.00897 -0.0135 1.0000 0.7709
-1.000 -0.2502 0.01492 0.00976 -0.0087 1.0000 0.7863
-0.750 -0.2435 0.01578 0.01065 -0.0028 1.0000 0.8025
-0.500 -0.2426 0.01641 0.01132 0.0045 1.0000 0.8137
-0.250 -0.2289 0.01670 0.01161 0.0081 1.0000 0.8243
0.000 -0.2063 0.01684 0.01172 0.0092 1.0000 0.8331
0.250 -0.1894 0.01688 0.01176 0.0117 1.0000 0.8399
0.500 -0.1682 0.01704 0.01191 0.0130 1.0000 0.8498
0.750 -0.1568 0.01704 0.01193 0.0169 1.0000 0.8582
1.000 -0.1316 0.01714 0.01203 0.0171 1.0000 0.8673
1.250 -0.1162 0.01703 0.01194 0.0196 1.0000 0.8729
1.500 -0.0807 0.01714 0.01207 0.0176 0.9969 0.8775
1.750 -0.0214 0.01741 0.01235 0.0109 0.9861 0.8802
2.000 0.0436 0.01733 0.01230 0.0038 0.9690 0.8816
2.250 0.0904 0.01693 0.01195 0.0006 0.9544 0.8835
2.500 0.1347 0.01654 0.01164 -0.0022 0.9436 0.8856
2.750 0.1799 0.01602 0.01120 -0.0050 0.9310 0.8876
3.000 0.2210 0.01542 0.01070 -0.0069 0.9157 0.8901
3.250 0.2533 0.01486 0.01024 -0.0071 0.8935 0.8930
3.500 0.2892 0.01418 0.00964 -0.0078 0.8599 0.8953
3.750 0.3757 0.01447 0.00858 -0.0168 0.5220 0.8934
4.000 0.3827 0.01541 0.00865 -0.0130 0.3459 0.8970
4.250 0.3980 0.01606 0.00877 -0.0108 0.2440 0.9000
4.500 0.4192 0.01653 0.00895 -0.0099 0.1909 0.9031
4.750 0.4442 0.01693 0.00918 -0.0098 0.1570 0.9063
5.000 0.4704 0.01732 0.00943 -0.0100 0.1300 0.9088
5.250 0.4918 0.01757 0.00956 -0.0089 0.1007 0.9111
5.500 0.5132 0.01818 0.00997 -0.0077 0.0614 0.9141
5.750 0.5366 0.01885 0.01054 -0.0070 0.0481 0.9170
6.000 0.5614 0.01968 0.01130 -0.0067 0.0425 0.9193
6.250 0.5887 0.02048 0.01213 -0.0069 0.0389 0.9213
6.500 0.6089 0.02122 0.01283 -0.0055 0.0363 0.9238
6.750 0.6328 0.02183 0.01353 -0.0048 0.0337 0.9264
7.000 0.6583 0.02300 0.01461 -0.0047 0.0320 0.9286
7.250 0.6859 0.02427 0.01603 -0.0048 0.0311 0.9305
7.500 0.7139 0.02570 0.01769 -0.0049 0.0304 0.9325
7.750 0.7382 0.02723 0.01948 -0.0042 0.0301 0.9347
8.000 0.7595 0.02900 0.02156 -0.0030 0.0300 0.9372
8.250 0.7802 0.03128 0.02422 -0.0019 0.0302 0.9393
8.500 0.7990 0.03398 0.02729 -0.0007 0.0308 0.9414
8.750 0.8168 0.03701 0.03060 0.0001 0.0314 0.9434
9.000 0.8152 0.04419 0.03884 0.0043 0.0377 0.9460
9.250 0.7317 0.06754 0.06407 0.0110 0.0691 0.9505
9.500 0.7353 0.07076 0.06737 0.0110 0.0680 0.9528
9.750 0.7433 0.07376 0.07038 0.0111 0.0671 0.9547
10.000 0.7661 0.07707 0.07356 0.0110 0.0662 0.9560
10.250 0.7540 0.08270 0.07927 0.0110 0.0656 0.9584
10.500 0.7065 0.08882 0.08568 0.0073 0.0653 0.9630
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Polar data table (+)
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