EPPLER 636 AIRFOIL (e636-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 636 AIRFOIL (e636-il) Reynolds number: 200,000 Max Cl/Cd: 61.72 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e636-il-200000.txt Download as CSV file: xf-e636-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 636 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4394 0.10923 0.10596 -0.0029 1.0000 0.0391
-9.750 -0.4441 0.10536 0.10215 -0.0076 1.0000 0.0395
-9.500 -0.4507 0.10099 0.09783 -0.0128 1.0000 0.0397
-9.250 -0.4550 0.09639 0.09326 -0.0175 1.0000 0.0398
-9.000 -0.4353 0.09263 0.08953 -0.0099 1.0000 0.0414
-8.750 -0.4290 0.08959 0.08653 -0.0100 1.0000 0.0425
-8.500 -0.4280 0.08602 0.08300 -0.0117 1.0000 0.0435
-8.250 -0.4317 0.08198 0.07902 -0.0147 1.0000 0.0441
-8.000 -0.4389 0.07806 0.07513 -0.0171 1.0000 0.0447
-7.750 -0.4474 0.07459 0.07167 -0.0176 1.0000 0.0457
-7.500 -0.4509 0.07107 0.06814 -0.0183 1.0000 0.0466
-7.250 -0.4534 0.06740 0.06439 -0.0192 1.0000 0.0484
-7.000 -0.4609 0.06578 0.06236 -0.0185 1.0000 0.0502
-6.750 -0.4420 0.05782 0.05432 -0.0228 0.9176 0.0515
-6.500 -0.4191 0.05426 0.05063 -0.0242 0.8530 0.0529
-6.250 -0.4086 0.05200 0.04814 -0.0226 0.8124 0.0547
-6.000 -0.3987 0.04968 0.04556 -0.0209 0.7835 0.0570
-5.750 -0.3883 0.05073 0.04575 -0.0169 0.7609 0.0628
-5.500 -0.3813 0.04428 0.03925 -0.0162 0.7430 0.0646
-5.250 -0.3655 0.04173 0.03666 -0.0152 0.7237 0.0665
-5.000 -0.3492 0.03979 0.03453 -0.0137 0.7065 0.0700
-4.750 -0.3361 0.03810 0.03222 -0.0108 0.6920 0.0782
-4.500 -0.3174 0.03555 0.02970 -0.0102 0.6768 0.0813
-4.250 -0.3008 0.03446 0.02813 -0.0079 0.6636 0.0928
-4.000 -0.2806 0.03209 0.02575 -0.0072 0.6504 0.0966
-3.750 -0.2621 0.03075 0.02402 -0.0053 0.6386 0.1087
-3.500 -0.2400 0.02902 0.02223 -0.0044 0.6256 0.1150
-3.250 -0.2020 0.02309 0.01492 -0.0002 0.6172 0.0478
-3.000 -0.1746 0.02094 0.01238 0.0008 0.6070 0.0442
-2.750 -0.1456 0.01940 0.01053 0.0014 0.5957 0.0425
-2.500 -0.1183 0.01856 0.00957 0.0018 0.5848 0.0440
-2.250 -0.0909 0.01780 0.00867 0.0023 0.5751 0.0456
-2.000 -0.0637 0.01694 0.00772 0.0029 0.5649 0.0460
-1.750 -0.0379 0.01626 0.00698 0.0036 0.5558 0.0471
-1.500 -0.0133 0.01574 0.00635 0.0046 0.5476 0.0488
-1.250 0.0104 0.01523 0.00581 0.0057 0.5386 0.0512
-1.000 0.0334 0.01480 0.00530 0.0068 0.5314 0.0583
-0.750 0.2734 0.01305 0.00619 -0.0319 0.5085 1.0000
-0.500 0.2961 0.01305 0.00600 -0.0312 0.5019 1.0000
-0.250 0.3191 0.01305 0.00591 -0.0305 0.4947 1.0000
0.000 0.3422 0.01307 0.00580 -0.0297 0.4885 1.0000
0.250 0.3654 0.01312 0.00574 -0.0290 0.4824 1.0000
0.500 0.3887 0.01315 0.00569 -0.0284 0.4759 1.0000
0.750 0.4121 0.01324 0.00562 -0.0276 0.4707 1.0000
1.000 0.4356 0.01329 0.00566 -0.0270 0.4644 1.0000
1.250 0.4592 0.01336 0.00565 -0.0263 0.4591 1.0000
1.500 0.4829 0.01349 0.00568 -0.0257 0.4544 1.0000
1.750 0.5066 0.01356 0.00576 -0.0250 0.4483 1.0000
2.000 0.5303 0.01366 0.00578 -0.0244 0.4434 1.0000
2.250 0.5542 0.01383 0.00587 -0.0237 0.4389 1.0000
2.500 0.5780 0.01394 0.00602 -0.0231 0.4336 1.0000
2.750 0.6019 0.01406 0.00609 -0.0225 0.4288 1.0000
3.000 0.6259 0.01425 0.00619 -0.0219 0.4247 1.0000
3.250 0.6496 0.01439 0.00640 -0.0213 0.4194 1.0000
3.500 0.6736 0.01454 0.00654 -0.0206 0.4150 1.0000
3.750 0.6977 0.01474 0.00665 -0.0200 0.4112 1.0000
4.000 0.7213 0.01494 0.00693 -0.0194 0.4064 1.0000
4.250 0.7450 0.01511 0.00713 -0.0188 0.4016 1.0000
4.500 0.7691 0.01530 0.00729 -0.0182 0.3977 1.0000
4.750 0.7929 0.01558 0.00756 -0.0175 0.3939 1.0000
5.000 0.8159 0.01580 0.00789 -0.0168 0.3890 1.0000
5.250 0.8395 0.01600 0.00809 -0.0162 0.3847 1.0000
5.500 0.8636 0.01627 0.00832 -0.0156 0.3812 1.0000
5.750 0.8861 0.01658 0.00876 -0.0148 0.3766 1.0000
6.000 0.9090 0.01683 0.00908 -0.0141 0.3720 1.0000
6.250 0.9326 0.01705 0.00929 -0.0134 0.3681 1.0000
6.500 0.9558 0.01741 0.00968 -0.0127 0.3642 1.0000
6.750 0.9775 0.01771 0.01014 -0.0118 0.3591 1.0000
7.000 1.0005 0.01793 0.01040 -0.0111 0.3548 1.0000
7.250 1.0247 0.01823 0.01062 -0.0105 0.3508 1.0000
7.500 1.0447 0.01853 0.01116 -0.0094 0.3450 1.0000
7.750 1.0673 0.01869 0.01136 -0.0085 0.3399 1.0000
8.000 1.0909 0.01897 0.01159 -0.0079 0.3357 1.0000
8.250 1.1103 0.01929 0.01215 -0.0066 0.3298 1.0000
8.500 1.1327 0.01944 0.01233 -0.0058 0.3247 1.0000
8.750 1.1546 0.01973 0.01266 -0.0049 0.3197 1.0000
9.000 1.1740 0.01997 0.01308 -0.0036 0.3133 1.0000
9.250 1.1971 0.02006 0.01314 -0.0029 0.3079 1.0000
9.500 1.2148 0.02037 0.01366 -0.0014 0.3010 1.0000
9.750 1.2360 0.02045 0.01377 -0.0004 0.2947 1.0000
10.000 1.2540 0.02072 0.01420 0.0011 0.2877 1.0000
10.250 1.2735 0.02080 0.01435 0.0024 0.2804 1.0000
10.500 1.2901 0.02107 0.01478 0.0040 0.2723 1.0000
10.750 1.3085 0.02120 0.01489 0.0054 0.2644 1.0000
11.000 1.3220 0.02147 0.01538 0.0074 0.2542 1.0000
11.250 1.3351 0.02175 0.01577 0.0094 0.2429 1.0000
11.500 1.3462 0.02210 0.01622 0.0117 0.2301 1.0000
11.750 1.3546 0.02263 0.01681 0.0142 0.2163 1.0000
12.000 1.3594 0.02333 0.01756 0.0171 0.2020 1.0000
12.250 1.3594 0.02425 0.01850 0.0205 0.1881 1.0000
12.500 1.3501 0.02534 0.01959 0.0250 0.1756 1.0000
12.750 1.3397 0.02694 0.02119 0.0283 0.1635 1.0000
13.000 1.3287 0.02917 0.02342 0.0303 0.1522 1.0000
13.250 1.3170 0.03201 0.02626 0.0312 0.1420 1.0000
13.500 1.3071 0.03508 0.02939 0.0315 0.1323 1.0000
13.750 1.2938 0.03875 0.03309 0.0313 0.1229 1.0000
14.000 1.2803 0.04260 0.03696 0.0309 0.1170 1.0000
14.250 1.2675 0.04655 0.04096 0.0303 0.1091 1.0000
14.500 1.2512 0.05094 0.04535 0.0295 0.1037 1.0000
14.750 1.2396 0.05495 0.04946 0.0287 0.0970 1.0000
15.000 1.2228 0.05960 0.05410 0.0276 0.0917 1.0000
15.250 1.2120 0.06377 0.05836 0.0265 0.0858 1.0000
15.500 1.1982 0.06844 0.06305 0.0252 0.0808 1.0000
15.750 1.1872 0.07291 0.06760 0.0239 0.0753 1.0000
16.000 1.1726 0.07802 0.07272 0.0221 0.0696 1.0000
16.250 1.1621 0.08260 0.07736 0.0207 0.0645 1.0000
16.500 1.1486 0.08779 0.08257 0.0189 0.0591 1.0000
16.750 1.1337 0.09330 0.08812 0.0169 0.0523 1.0000
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