BE50 (original) (be50-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: BE50 (original) (be50-il) Reynolds number: 100,000 Max Cl/Cd: 59.65 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-be50-il-100000-n5.txt Download as CSV file: xf-be50-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BE50 (original)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3641 0.09306 0.08829 -0.0226 1.0000 0.0506
-8.000 -0.3703 0.09112 0.08647 -0.0264 1.0000 0.0534
-7.750 -0.3677 0.08805 0.08348 -0.0312 1.0000 0.0540
-7.500 -0.3613 0.08438 0.07984 -0.0349 1.0000 0.0541
-7.250 -0.3583 0.07890 0.07436 -0.0305 1.0000 0.0396
-7.000 -0.3514 0.07503 0.07053 -0.0336 1.0000 0.0397
-6.750 -0.3409 0.07068 0.06618 -0.0378 1.0000 0.0400
-6.500 -0.3298 0.06646 0.06197 -0.0407 1.0000 0.0397
-6.250 -0.3171 0.06228 0.05776 -0.0433 1.0000 0.0388
-6.000 -0.2987 0.05727 0.05268 -0.0480 1.0000 0.0380
-5.750 -0.2737 0.05138 0.04662 -0.0542 1.0000 0.0376
-5.500 -0.2369 0.04355 0.03838 -0.0634 1.0000 0.0395
-5.250 -0.2021 0.03722 0.03151 -0.0695 1.0000 0.0401
-5.000 -0.1684 0.03232 0.02599 -0.0736 1.0000 0.0403
-4.750 -0.1271 0.02829 0.02133 -0.0786 0.9973 0.0428
-4.500 -0.0871 0.02581 0.01842 -0.0821 0.9939 0.0444
-4.250 -0.0474 0.02350 0.01560 -0.0851 0.9901 0.0451
-4.000 -0.0076 0.02175 0.01341 -0.0878 0.9866 0.0463
-3.750 0.0302 0.02038 0.01173 -0.0899 0.9817 0.0477
-3.500 0.0692 0.01944 0.01054 -0.0923 0.9771 0.0517
-3.250 0.1065 0.01855 0.00941 -0.0941 0.9707 0.0539
-3.000 0.1469 0.01756 0.00837 -0.0967 0.9653 0.0558
-2.750 0.1844 0.01685 0.00765 -0.0987 0.9567 0.0590
-2.500 0.2259 0.01623 0.00693 -0.1013 0.9496 0.0646
-2.250 0.2626 0.01564 0.00634 -0.1029 0.9392 0.0752
-2.000 0.2975 0.01499 0.00593 -0.1043 0.9277 0.1259
-1.750 0.3311 0.01440 0.00562 -0.1054 0.9157 0.2233
-1.500 0.3637 0.01371 0.00559 -0.1064 0.9032 0.4224
-1.250 0.3933 0.01304 0.00546 -0.1064 0.8890 0.5919
-1.000 0.4162 0.01203 0.00511 -0.1041 0.8718 1.0000
-0.750 0.4485 0.01197 0.00484 -0.1045 0.8547 1.0000
-0.500 0.4795 0.01195 0.00463 -0.1047 0.8368 1.0000
-0.250 0.5098 0.01195 0.00447 -0.1047 0.8188 1.0000
0.000 0.5399 0.01198 0.00432 -0.1047 0.8002 1.0000
0.250 0.5694 0.01203 0.00422 -0.1046 0.7808 1.0000
0.500 0.5978 0.01212 0.00418 -0.1043 0.7602 1.0000
0.750 0.6262 0.01224 0.00414 -0.1040 0.7393 1.0000
1.000 0.6537 0.01239 0.00418 -0.1036 0.7173 1.0000
1.250 0.6809 0.01258 0.00423 -0.1031 0.6952 1.0000
1.500 0.7076 0.01278 0.00433 -0.1026 0.6712 1.0000
1.750 0.7341 0.01300 0.00445 -0.1020 0.6464 1.0000
2.000 0.7602 0.01325 0.00460 -0.1014 0.6200 1.0000
2.250 0.7861 0.01352 0.00476 -0.1008 0.5914 1.0000
2.500 0.8116 0.01381 0.00494 -0.1002 0.5608 1.0000
2.750 0.8369 0.01415 0.00514 -0.0995 0.5300 1.0000
3.000 0.8620 0.01451 0.00542 -0.0989 0.5002 1.0000
3.250 0.8872 0.01489 0.00572 -0.0983 0.4691 1.0000
3.500 0.9121 0.01529 0.00603 -0.0978 0.4399 1.0000
3.750 0.9368 0.01574 0.00637 -0.0972 0.4163 1.0000
4.000 0.9615 0.01623 0.00681 -0.0966 0.3969 1.0000
4.250 0.9862 0.01673 0.00727 -0.0961 0.3803 1.0000
4.500 1.0109 0.01725 0.00778 -0.0956 0.3656 1.0000
4.750 1.0358 0.01777 0.00833 -0.0951 0.3520 1.0000
5.000 1.0606 0.01829 0.00894 -0.0946 0.3390 1.0000
5.250 1.0853 0.01883 0.00956 -0.0941 0.3265 1.0000
5.500 1.1093 0.01937 0.01017 -0.0935 0.3109 1.0000
5.750 1.1322 0.01989 0.01072 -0.0928 0.2905 1.0000
6.000 1.1555 0.02031 0.01131 -0.0922 0.2667 1.0000
6.250 1.1778 0.02078 0.01181 -0.0914 0.2368 1.0000
6.500 1.1977 0.02152 0.01236 -0.0905 0.1904 1.0000
6.750 1.2154 0.02276 0.01326 -0.0894 0.1253 1.0000
7.000 1.2255 0.02530 0.01507 -0.0875 0.0426 1.0000
7.250 1.2408 0.02704 0.01683 -0.0858 0.0290 1.0000
7.500 1.2553 0.02876 0.01870 -0.0840 0.0246 1.0000
7.750 1.2702 0.03025 0.02049 -0.0823 0.0227 1.0000
8.000 1.2837 0.03177 0.02226 -0.0804 0.0211 1.0000
8.250 1.2956 0.03333 0.02401 -0.0785 0.0193 1.0000
8.500 1.3048 0.03503 0.02587 -0.0764 0.0179 1.0000
8.750 1.3077 0.03720 0.02819 -0.0737 0.0169 1.0000
9.000 1.3119 0.03908 0.03024 -0.0709 0.0165 1.0000
9.250 1.3143 0.04106 0.03240 -0.0680 0.0161 1.0000
9.500 1.3168 0.04322 0.03473 -0.0654 0.0158 1.0000
9.750 1.3197 0.04554 0.03722 -0.0631 0.0156 1.0000
10.000 1.3229 0.04803 0.03990 -0.0610 0.0153 1.0000
10.250 1.3259 0.05069 0.04276 -0.0592 0.0151 1.0000
10.500 1.3279 0.05357 0.04592 -0.0575 0.0149 1.0000
10.750 1.3281 0.05667 0.04924 -0.0560 0.0147 1.0000
11.000 1.3260 0.05999 0.05281 -0.0549 0.0144 1.0000
11.250 1.3216 0.06358 0.05664 -0.0542 0.0141 1.0000
11.500 1.3152 0.06748 0.06077 -0.0540 0.0138 1.0000
11.750 1.3068 0.07181 0.06534 -0.0544 0.0136 1.0000
12.000 1.2966 0.07654 0.07030 -0.0554 0.0135 1.0000
12.250 1.2850 0.08174 0.07573 -0.0570 0.0133 1.0000
12.500 1.2718 0.08748 0.08169 -0.0592 0.0132 1.0000
12.750 1.2572 0.09378 0.08821 -0.0621 0.0132 1.0000
13.000 1.2412 0.10072 0.09538 -0.0657 0.0133 1.0000
13.250 1.2239 0.10837 0.10325 -0.0701 0.0134 1.0000
13.500 1.2041 0.11731 0.11242 -0.0755 0.0136 1.0000
13.750 1.1830 0.12731 0.12262 -0.0819 0.0139 1.0000
14.000 1.1611 0.13827 0.13376 -0.0890 0.0144 1.0000
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Polar data table (+)
Polar graphs
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