EPPLER 344 AIRFOIL (e344-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 344 AIRFOIL (e344-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.86 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e344-il-1000000-n5.txt Download as CSV file: xf-e344-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 344 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1858 0.09487 0.09150 -0.0638 0.5861 0.0078
-10.250 -0.1963 0.08840 0.08504 -0.0656 0.5818 0.0058
-10.000 -0.1947 0.08534 0.08197 -0.0669 0.5737 0.0059
-9.750 -0.1800 0.08516 0.08174 -0.0671 0.5615 0.0064
-9.500 -0.1967 0.07785 0.07446 -0.0703 0.5600 0.0060
-9.250 -0.1913 0.07571 0.07231 -0.0714 0.5523 0.0062
-8.750 -0.2196 0.06515 0.06176 -0.0786 0.5409 0.0061
-8.500 -0.2272 0.06232 0.05891 -0.0788 0.5365 0.0063
-8.250 -0.2540 0.05810 0.05464 -0.0763 0.5312 0.0061
-8.000 -0.2537 0.05595 0.05242 -0.0752 0.5253 0.0063
-7.750 -0.2718 0.05026 0.04659 -0.0728 0.5221 0.0061
-7.500 -0.2682 0.04764 0.04386 -0.0712 0.5160 0.0063
-7.000 -0.3386 0.02309 0.01789 -0.0552 0.5169 0.0059
-6.500 -0.3069 0.01896 0.01309 -0.0512 0.5042 0.0059
-6.250 -0.2858 0.01778 0.01167 -0.0499 0.4973 0.0059
-6.000 -0.2638 0.01669 0.01037 -0.0489 0.4912 0.0059
-5.750 -0.2404 0.01582 0.00933 -0.0480 0.4848 0.0059
-5.250 -0.1919 0.01448 0.00771 -0.0465 0.4718 0.0059
-5.000 -0.1675 0.01386 0.00695 -0.0458 0.4648 0.0059
-4.750 -0.1430 0.01328 0.00627 -0.0450 0.4588 0.0059
-4.500 -0.1181 0.01281 0.00572 -0.0444 0.4536 0.0059
-4.250 -0.0935 0.01240 0.00523 -0.0437 0.4479 0.0060
-4.000 -0.0687 0.01204 0.00479 -0.0430 0.4429 0.0060
-3.750 -0.0436 0.01172 0.00443 -0.0424 0.4383 0.0061
-3.500 -0.0187 0.01144 0.00409 -0.0417 0.4330 0.0062
-3.250 0.0064 0.01122 0.00382 -0.0411 0.4278 0.0063
-3.000 0.0318 0.01098 0.00355 -0.0406 0.4236 0.0064
-2.750 0.0574 0.01080 0.00334 -0.0400 0.4187 0.0066
-2.500 0.0829 0.01065 0.00314 -0.0395 0.4143 0.0067
-2.250 0.1086 0.01049 0.00295 -0.0390 0.4107 0.0071
-2.000 0.1347 0.01035 0.00279 -0.0386 0.4073 0.0074
-1.750 0.1608 0.01024 0.00265 -0.0381 0.4035 0.0078
-1.500 0.1866 0.01012 0.00250 -0.0377 0.3994 0.0085
-1.250 0.2127 0.01005 0.00241 -0.0373 0.3955 0.0098
-1.000 0.2392 0.00996 0.00231 -0.0369 0.3924 0.0113
-0.750 0.2656 0.00988 0.00224 -0.0366 0.3891 0.0146
-0.500 0.2918 0.00981 0.00218 -0.0363 0.3859 0.0222
-0.250 0.3177 0.00973 0.00214 -0.0359 0.3828 0.0382
0.000 0.3433 0.00962 0.00212 -0.0355 0.3798 0.0691
0.250 0.3680 0.00938 0.00210 -0.0349 0.3776 0.1438
0.500 0.3600 0.00712 0.00208 -0.0283 0.3757 0.8377
0.750 0.3855 0.00729 0.00225 -0.0276 0.3727 0.8740
1.000 0.4115 0.00744 0.00238 -0.0270 0.3698 0.8833
1.250 0.4383 0.00758 0.00246 -0.0266 0.3670 0.8910
1.500 0.4626 0.00776 0.00264 -0.0256 0.3643 0.8987
1.750 0.4886 0.00791 0.00277 -0.0251 0.3625 0.9057
2.000 0.5165 0.00797 0.00279 -0.0251 0.3601 0.9072
2.250 0.5443 0.00801 0.00280 -0.0251 0.3575 0.9079
2.500 0.5720 0.00807 0.00282 -0.0252 0.3550 0.9084
2.750 0.5995 0.00813 0.00285 -0.0252 0.3525 0.9090
3.000 0.6268 0.00822 0.00290 -0.0252 0.3497 0.9096
3.250 0.6545 0.00828 0.00294 -0.0253 0.3477 0.9101
3.500 0.6821 0.00833 0.00299 -0.0253 0.3457 0.9109
3.750 0.7096 0.00840 0.00305 -0.0253 0.3436 0.9116
4.000 0.7371 0.00847 0.00310 -0.0254 0.3411 0.9122
4.250 0.7643 0.00856 0.00317 -0.0254 0.3385 0.9128
4.500 0.7912 0.00866 0.00325 -0.0254 0.3359 0.9134
4.750 0.8180 0.00876 0.00334 -0.0254 0.3334 0.9140
5.000 0.8456 0.00883 0.00341 -0.0255 0.3315 0.9147
5.250 0.8729 0.00890 0.00349 -0.0256 0.3293 0.9153
5.500 0.8999 0.00899 0.00357 -0.0256 0.3267 0.9159
5.750 0.9267 0.00909 0.00367 -0.0256 0.3241 0.9166
6.000 0.9530 0.00921 0.00378 -0.0255 0.3211 0.9173
6.250 0.9792 0.00933 0.00390 -0.0255 0.3183 0.9180
6.500 1.0061 0.00942 0.00401 -0.0255 0.3162 0.9189
6.750 1.0328 0.00952 0.00412 -0.0255 0.3135 0.9196
7.000 1.0590 0.00963 0.00424 -0.0255 0.3105 0.9203
7.250 1.0847 0.00977 0.00438 -0.0254 0.3069 0.9209
7.500 1.1100 0.00992 0.00453 -0.0252 0.3036 0.9215
7.750 1.1364 0.01003 0.00466 -0.0252 0.3006 0.9221
8.000 1.1619 0.01015 0.00480 -0.0251 0.2969 0.9227
8.250 1.1865 0.01030 0.00496 -0.0248 0.2930 0.9235
8.500 1.2103 0.01047 0.00513 -0.0243 0.2887 0.9243
8.750 1.2350 0.01059 0.00530 -0.0241 0.2853 0.9251
9.000 1.2586 0.01077 0.00548 -0.0236 0.2800 0.9260
9.250 1.2809 0.01098 0.00569 -0.0229 0.2744 0.9269
9.500 1.3038 0.01117 0.00590 -0.0224 0.2679 0.9279
9.750 1.3246 0.01143 0.00615 -0.0215 0.2617 0.9290
10.000 1.3460 0.01164 0.00638 -0.0207 0.2549 0.9301
10.250 1.3633 0.01192 0.00665 -0.0191 0.2477 0.9317
10.500 1.3817 0.01218 0.00692 -0.0178 0.2404 0.9333
10.750 1.3975 0.01254 0.00727 -0.0161 0.2325 0.9350
11.000 1.4139 0.01288 0.00762 -0.0145 0.2246 0.9364
11.250 1.4274 0.01332 0.00804 -0.0125 0.2149 0.9382
11.500 1.4381 0.01382 0.00853 -0.0101 0.2050 0.9405
11.750 1.4476 0.01438 0.00908 -0.0075 0.1946 0.9431
12.000 1.4580 0.01493 0.00963 -0.0053 0.1856 0.9459
12.250 1.4661 0.01559 0.01030 -0.0028 0.1773 0.9491
12.500 1.4707 0.01641 0.01110 -0.0001 0.1676 0.9529
12.750 1.4770 0.01719 0.01192 0.0023 0.1594 0.9580
13.000 1.4800 0.01830 0.01303 0.0047 0.1499 0.9652
13.250 1.4881 0.01963 0.01438 0.0054 0.1408 0.9747
13.500 1.5016 0.02120 0.01596 0.0045 0.1310 0.9912
14.000 1.5029 0.02486 0.01965 0.0069 0.1172 1.0000
14.250 1.5029 0.02693 0.02175 0.0077 0.1109 1.0000
14.500 1.4969 0.02961 0.02445 0.0085 0.1042 1.0000
14.750 1.4908 0.03244 0.02731 0.0091 0.0975 1.0000
15.000 1.4838 0.03546 0.03037 0.0095 0.0929 1.0000
15.250 1.4759 0.03863 0.03359 0.0098 0.0876 1.0000
15.500 1.4642 0.04228 0.03729 0.0099 0.0832 1.0000
15.750 1.4559 0.04568 0.04075 0.0099 0.0792 1.0000
16.000 1.4477 0.04919 0.04432 0.0096 0.0764 1.0000
16.250 1.4350 0.05329 0.04847 0.0093 0.0727 1.0000
16.500 1.4259 0.05708 0.05232 0.0088 0.0689 1.0000
16.750 1.4146 0.06122 0.05650 0.0081 0.0655 1.0000
17.000 1.4029 0.06552 0.06084 0.0073 0.0615 1.0000
17.250 1.3962 0.06929 0.06467 0.0065 0.0591 1.0000
17.500 1.3839 0.07383 0.06925 0.0054 0.0554 1.0000
17.750 1.3766 0.07784 0.07331 0.0044 0.0525 1.0000
18.000 1.3684 0.08198 0.07750 0.0032 0.0489 1.0000
18.250 1.3596 0.08633 0.08188 0.0019 0.0465 1.0000
18.500 1.3551 0.09015 0.08577 0.0006 0.0442 1.0000
18.750 1.3495 0.09416 0.08982 -0.0007 0.0416 1.0000
19.000 1.3410 0.09863 0.09433 -0.0023 0.0389 1.0000
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Polar data table (+)
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