FX 79-W-151 A (fx79w151a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 79-W-151 A (fx79w151a-il) Reynolds number: 500,000 Max Cl/Cd: 102.03 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx79w151a-il-500000-n5.txt Download as CSV file: xf-fx79w151a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 79-W-151 A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.7312 0.08212 0.07911 -0.0548 1.0000 0.0090
-15.000 -0.7830 0.07010 0.06696 -0.0620 1.0000 0.0089
-14.750 -0.8321 0.05782 0.05449 -0.0699 1.0000 0.0087
-14.500 -0.8702 0.04574 0.04215 -0.0800 1.0000 0.0087
-14.250 -0.8943 0.03823 0.03440 -0.0865 1.0000 0.0086
-14.000 -0.8927 0.03419 0.03018 -0.0909 0.9743 0.0087
-13.750 -0.8740 0.03076 0.02649 -0.0970 0.9524 0.0089
-13.500 -0.8521 0.02885 0.02440 -0.1002 0.9343 0.0092
-13.250 -0.8423 0.02718 0.02252 -0.1004 0.9145 0.0093
-13.000 -0.8390 0.02588 0.02104 -0.0984 0.8971 0.0095
-12.750 -0.8351 0.02486 0.01986 -0.0957 0.8829 0.0095
-12.500 -0.8288 0.02403 0.01888 -0.0929 0.8707 0.0099
-12.250 -0.8228 0.02324 0.01795 -0.0898 0.8597 0.0102
-12.000 -0.8147 0.02257 0.01713 -0.0870 0.8498 0.0103
-11.750 -0.8069 0.02161 0.01603 -0.0843 0.8405 0.0108
-11.500 -0.7941 0.02085 0.01516 -0.0822 0.8322 0.0112
-11.250 -0.7788 0.02023 0.01442 -0.0805 0.8244 0.0115
-11.000 -0.7624 0.01960 0.01370 -0.0788 0.8163 0.0122
-10.750 -0.7451 0.01904 0.01301 -0.0773 0.8089 0.0129
-10.500 -0.7266 0.01849 0.01236 -0.0759 0.8014 0.0133
-10.250 -0.7086 0.01788 0.01164 -0.0744 0.7941 0.0142
-10.000 -0.6893 0.01732 0.01102 -0.0732 0.7868 0.0152
-9.750 -0.6690 0.01685 0.01045 -0.0720 0.7798 0.0162
-9.500 -0.6477 0.01641 0.00990 -0.0710 0.7730 0.0175
-9.250 -0.6269 0.01593 0.00934 -0.0699 0.7659 0.0190
-9.000 -0.6051 0.01551 0.00886 -0.0689 0.7594 0.0207
-8.750 -0.5823 0.01516 0.00842 -0.0681 0.7524 0.0225
-8.500 -0.5601 0.01476 0.00795 -0.0672 0.7461 0.0244
-8.250 -0.5370 0.01440 0.00754 -0.0664 0.7390 0.0268
-8.000 -0.5135 0.01412 0.00717 -0.0656 0.7323 0.0290
-7.750 -0.4903 0.01374 0.00677 -0.0649 0.7256 0.0321
-7.500 -0.4665 0.01346 0.00642 -0.0642 0.7191 0.0353
-7.250 -0.4425 0.01316 0.00608 -0.0635 0.7131 0.0387
-7.000 -0.4185 0.01287 0.00576 -0.0629 0.7063 0.0429
-6.750 -0.3943 0.01261 0.00545 -0.0622 0.7001 0.0479
-6.500 -0.3697 0.01236 0.00519 -0.0617 0.6933 0.0541
-6.250 -0.3452 0.01213 0.00493 -0.0611 0.6871 0.0606
-6.000 -0.3199 0.01193 0.00471 -0.0606 0.6804 0.0666
-5.750 -0.2950 0.01173 0.00449 -0.0601 0.6739 0.0733
-5.500 -0.2694 0.01159 0.00430 -0.0597 0.6680 0.0787
-5.250 -0.2440 0.01141 0.00410 -0.0592 0.6615 0.0843
-5.000 -0.2184 0.01129 0.00393 -0.0588 0.6552 0.0904
-4.750 -0.1925 0.01116 0.00375 -0.0584 0.6489 0.0950
-4.500 -0.1671 0.01102 0.00359 -0.0579 0.6427 0.1007
-4.250 -0.1409 0.01092 0.00345 -0.0576 0.6366 0.1060
-4.000 -0.1154 0.01079 0.00330 -0.0572 0.6300 0.1121
-3.750 -0.0896 0.01069 0.00316 -0.0568 0.6244 0.1179
-3.500 -0.0634 0.01059 0.00303 -0.0564 0.6184 0.1234
-3.250 -0.0378 0.01048 0.00292 -0.0560 0.6126 0.1316
-3.000 -0.0118 0.01039 0.00280 -0.0557 0.6071 0.1384
-2.750 0.0141 0.01029 0.00269 -0.0553 0.6011 0.1462
-2.250 0.0659 0.01012 0.00251 -0.0546 0.5900 0.1666
-2.000 0.0916 0.01002 0.00243 -0.0542 0.5844 0.1813
-1.500 0.1425 0.00980 0.00230 -0.0533 0.5737 0.2213
-1.250 0.1676 0.00969 0.00225 -0.0528 0.5683 0.2496
-1.000 0.1925 0.00957 0.00221 -0.0523 0.5636 0.2802
-0.750 0.2175 0.00943 0.00217 -0.0519 0.5585 0.3174
-0.500 0.2415 0.00928 0.00214 -0.0512 0.5528 0.3630
-0.250 0.2646 0.00908 0.00212 -0.0503 0.5481 0.4256
0.000 0.2872 0.00886 0.00212 -0.0494 0.5429 0.4945
0.250 0.3091 0.00869 0.00212 -0.0482 0.5378 0.5579
0.500 0.3304 0.00852 0.00214 -0.0469 0.5330 0.6195
0.750 0.3513 0.00834 0.00217 -0.0454 0.5278 0.6841
1.000 0.3717 0.00816 0.00222 -0.0438 0.5230 0.7562
1.250 0.3978 0.00803 0.00229 -0.0433 0.5185 0.8226
1.500 0.4476 0.00799 0.00242 -0.0481 0.5128 0.8866
1.750 0.5220 0.00815 0.00258 -0.0583 0.5059 0.9267
2.000 0.5678 0.00831 0.00272 -0.0622 0.5002 0.9433
2.250 0.6030 0.00847 0.00286 -0.0638 0.4947 0.9563
2.500 0.6377 0.00866 0.00301 -0.0652 0.4898 0.9686
2.750 0.6707 0.00880 0.00314 -0.0664 0.4847 0.9770
3.000 0.7073 0.00892 0.00323 -0.0685 0.4788 0.9798
3.250 0.7413 0.00906 0.00333 -0.0700 0.4734 0.9836
3.500 0.7743 0.00917 0.00344 -0.0713 0.4681 0.9873
3.750 0.8104 0.00928 0.00354 -0.0733 0.4628 0.9896
4.000 0.8456 0.00941 0.00365 -0.0751 0.4580 0.9925
4.250 0.8806 0.00953 0.00378 -0.0769 0.4524 0.9955
4.500 0.9159 0.00967 0.00390 -0.0788 0.4467 0.9984
4.750 0.9489 0.00979 0.00402 -0.0802 0.4418 1.0000
5.000 0.9710 0.00990 0.00415 -0.0793 0.4372 1.0000
5.250 0.9925 0.01004 0.00429 -0.0782 0.4325 1.0000
5.500 1.0137 0.01019 0.00445 -0.0771 0.4284 1.0000
5.750 1.0356 0.01031 0.00460 -0.0761 0.4236 1.0000
6.000 1.0567 0.01047 0.00477 -0.0750 0.4187 1.0000
6.250 1.0770 0.01066 0.00496 -0.0737 0.4144 1.0000
6.500 1.0987 0.01080 0.00515 -0.0727 0.4100 1.0000
6.750 1.1193 0.01097 0.00535 -0.0715 0.4053 1.0000
7.000 1.1388 0.01119 0.00557 -0.0700 0.4005 1.0000
7.250 1.1592 0.01137 0.00579 -0.0688 0.3951 1.0000
7.500 1.1767 0.01162 0.00603 -0.0670 0.3862 1.0000
7.750 1.1926 0.01191 0.00630 -0.0650 0.3730 1.0000
8.000 1.2054 0.01229 0.00662 -0.0625 0.3564 1.0000
8.250 1.2166 0.01271 0.00698 -0.0597 0.3380 1.0000
8.500 1.2232 0.01324 0.00741 -0.0561 0.3142 1.0000
8.750 1.2263 0.01376 0.00785 -0.0518 0.2955 1.0000
9.000 1.2281 0.01449 0.00846 -0.0478 0.2688 1.0000
9.250 1.2242 0.01567 0.00944 -0.0434 0.2302 1.0000
9.500 1.2215 0.01706 0.01065 -0.0396 0.1958 1.0000
9.750 1.2129 0.01899 0.01234 -0.0357 0.1541 1.0000
10.000 1.2095 0.02082 0.01401 -0.0328 0.1222 1.0000
10.250 1.2064 0.02279 0.01584 -0.0303 0.0936 1.0000
10.500 1.2058 0.02473 0.01768 -0.0283 0.0721 1.0000
10.750 1.2035 0.02689 0.01975 -0.0264 0.0518 1.0000
11.000 1.2008 0.02922 0.02200 -0.0248 0.0342 1.0000
11.250 1.2042 0.03112 0.02389 -0.0236 0.0261 1.0000
11.500 1.2065 0.03320 0.02598 -0.0226 0.0196 1.0000
11.750 1.2104 0.03519 0.02800 -0.0217 0.0163 1.0000
12.000 1.2159 0.03708 0.02994 -0.0209 0.0145 1.0000
12.250 1.2201 0.03916 0.03207 -0.0203 0.0129 1.0000
12.500 1.2244 0.04128 0.03424 -0.0197 0.0121 1.0000
12.750 1.2291 0.04341 0.03645 -0.0192 0.0110 1.0000
13.000 1.2337 0.04561 0.03872 -0.0188 0.0107 1.0000
13.250 1.2371 0.04798 0.04114 -0.0185 0.0100 1.0000
13.500 1.2405 0.05038 0.04362 -0.0182 0.0097 1.0000
13.750 1.2402 0.05323 0.04652 -0.0180 0.0090 1.0000
14.000 1.2424 0.05587 0.04926 -0.0178 0.0085 1.0000
14.250 1.2459 0.05840 0.05187 -0.0178 0.0084 1.0000
14.500 1.2474 0.06117 0.05471 -0.0178 0.0080 1.0000
14.750 1.2501 0.06386 0.05747 -0.0178 0.0075 1.0000
15.000 1.2493 0.06702 0.06072 -0.0179 0.0075 1.0000
15.250 1.2508 0.06992 0.06367 -0.0181 0.0071 1.0000
15.500 1.2503 0.07310 0.06692 -0.0184 0.0068 1.0000
15.750 1.2481 0.07655 0.07045 -0.0187 0.0068 1.0000
16.000 1.2434 0.08039 0.07437 -0.0192 0.0066 1.0000
16.250 1.2434 0.08365 0.07772 -0.0197 0.0067 1.0000
16.500 1.2446 0.08678 0.08094 -0.0202 0.0064 1.0000
16.750 1.2409 0.09061 0.08486 -0.0208 0.0063 1.0000
17.000 1.2417 0.09381 0.08814 -0.0214 0.0060 1.0000
17.250 1.2398 0.09746 0.09187 -0.0221 0.0058 1.0000
17.500 1.2386 0.10104 0.09553 -0.0229 0.0060 1.0000
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Polar data table (+)
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