CHEN AIRFOIL (chen-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CHEN AIRFOIL (chen-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.39 at α=14.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-chen-il-1000000.txt Download as CSV file: xf-chen-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: CHEN 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0197 0.11018 0.10570 -0.0601 0.3293 0.0119
-10.250 -0.0143 0.10686 0.10240 -0.0625 0.3291 0.0124
-10.000 -0.0071 0.10403 0.09958 -0.0645 0.3293 0.0124
-9.750 0.0543 0.09074 0.08657 -0.0643 0.3297 0.0124
-9.500 0.0634 0.08754 0.08337 -0.0640 0.3297 0.0127
-9.250 0.0191 0.09617 0.09175 -0.0686 0.3293 0.0124
-9.000 0.0283 0.09384 0.08943 -0.0697 0.3292 0.0124
-8.750 0.0391 0.09105 0.08665 -0.0698 0.3292 0.0129
-8.500 0.0482 0.08897 0.08459 -0.0706 0.3292 0.0131
-8.250 0.0555 0.08653 0.08216 -0.0716 0.3292 0.0132
-8.000 0.0640 0.08453 0.08018 -0.0723 0.3291 0.0136
-7.750 0.0702 0.08219 0.07787 -0.0732 0.3292 0.0138
-7.500 0.0761 0.08002 0.07572 -0.0738 0.3292 0.0139
-7.250 0.0791 0.07765 0.07338 -0.0746 0.3292 0.0149
-7.000 0.0798 0.07546 0.07123 -0.0750 0.3292 0.0149
-6.750 0.0711 0.07326 0.06906 -0.0741 0.3292 0.0154
-6.500 0.0644 0.07174 0.06756 -0.0728 0.3292 0.0155
-6.250 0.0661 0.06953 0.06536 -0.0722 0.3293 0.0156
-6.000 0.0702 0.06739 0.06323 -0.0715 0.3294 0.0156
-5.750 0.0764 0.06535 0.06117 -0.0708 0.3294 0.0156
-5.500 0.0772 0.06215 0.05796 -0.0696 0.3294 0.0158
-5.250 0.0854 0.06001 0.05581 -0.0686 0.3293 0.0158
-5.000 0.0960 0.05852 0.05433 -0.0673 0.3293 0.0161
-4.750 0.1072 0.05687 0.05265 -0.0663 0.3292 0.0162
-4.500 0.1188 0.05520 0.05097 -0.0652 0.3293 0.0164
-4.250 0.1314 0.05358 0.04933 -0.0640 0.3292 0.0168
-4.000 0.1444 0.05185 0.04756 -0.0628 0.3292 0.0172
-3.750 0.1578 0.04998 0.04565 -0.0614 0.3292 0.0180
-3.500 0.1677 0.04586 0.04135 -0.0585 0.3292 0.0194
-3.250 0.1820 0.04439 0.03985 -0.0569 0.3290 0.0197
-3.000 0.1985 0.04361 0.03908 -0.0557 0.3292 0.0201
-2.750 0.2151 0.04229 0.03770 -0.0541 0.3290 0.0204
-2.500 0.2323 0.04103 0.03640 -0.0525 0.3290 0.0210
-2.250 0.2524 0.03883 0.03403 -0.0498 0.3289 0.0233
-2.000 0.2071 0.01855 0.01196 -0.0327 0.3290 0.0196
-1.750 0.2340 0.01791 0.01120 -0.0323 0.3288 0.0200
-1.500 0.2595 0.01786 0.01115 -0.0317 0.3289 0.0207
-1.250 0.2865 0.01757 0.01080 -0.0313 0.3287 0.0213
-1.000 0.3129 0.01745 0.01064 -0.0308 0.3286 0.0221
-0.750 0.3392 0.01736 0.01052 -0.0303 0.3285 0.0229
-0.500 0.3648 0.01733 0.01046 -0.0296 0.3284 0.0233
-0.250 0.3905 0.01706 0.01016 -0.0290 0.3281 0.0245
0.000 0.4157 0.01703 0.01015 -0.0282 0.3277 0.0262
0.250 0.4400 0.01708 0.01019 -0.0273 0.3274 0.0275
0.500 0.4634 0.01714 0.01027 -0.0263 0.3274 0.0295
0.750 0.4867 0.01731 0.01048 -0.0252 0.3274 0.0317
1.000 0.5098 0.01742 0.01062 -0.0241 0.3271 0.0354
1.250 0.5329 0.01768 0.01091 -0.0230 0.3271 0.0394
1.500 0.5554 0.01794 0.01122 -0.0219 0.3271 0.0448
1.750 0.5783 0.01819 0.01148 -0.0209 0.3268 0.0486
2.000 0.6008 0.01848 0.01183 -0.0197 0.3267 0.0522
2.250 0.6235 0.01882 0.01220 -0.0187 0.3266 0.0552
2.500 0.6456 0.01908 0.01248 -0.0175 0.3265 0.0575
2.750 0.6683 0.01925 0.01270 -0.0165 0.3261 0.0611
3.000 0.6909 0.01957 0.01305 -0.0154 0.3259 0.0642
3.250 0.7134 0.01999 0.01350 -0.0145 0.3256 0.0668
3.500 0.7336 0.02026 0.01383 -0.0130 0.3255 0.0714
3.750 0.7548 0.02067 0.01428 -0.0119 0.3253 0.0753
4.000 0.7775 0.02093 0.01455 -0.0109 0.3249 0.0783
4.250 0.7982 0.02118 0.01485 -0.0096 0.3246 0.0834
4.500 0.8211 0.02135 0.01504 -0.0087 0.3241 0.0873
4.750 0.8427 0.02170 0.01541 -0.0076 0.3238 0.0907
5.000 0.8633 0.02206 0.01581 -0.0065 0.3236 0.0946
5.250 0.8842 0.02243 0.01622 -0.0053 0.3233 0.0994
5.500 0.9059 0.02274 0.01657 -0.0044 0.3230 0.1033
5.750 0.9270 0.02312 0.01698 -0.0033 0.3227 0.1069
6.000 0.9491 0.02341 0.01732 -0.0025 0.3224 0.1146
6.250 0.9708 0.02376 0.01771 -0.0016 0.3221 0.1235
6.500 0.9934 0.02404 0.01804 -0.0008 0.3218 0.1391
6.750 1.0160 0.02433 0.01837 -0.0001 0.3215 0.1552
7.000 1.0389 0.02461 0.01868 0.0006 0.3212 0.1681
7.250 1.0638 0.02475 0.01884 0.0009 0.3208 0.1811
7.500 1.0906 0.02477 0.01887 0.0010 0.3205 0.1942
8.500 1.3634 0.02496 0.02067 -0.0358 0.3154 0.9917
8.750 1.3876 0.02654 0.02236 -0.0367 0.3156 0.9944
9.000 1.4655 0.02536 0.02116 -0.0467 0.3136 0.9990
9.250 1.4935 0.02587 0.02173 -0.0476 0.3130 1.0000
9.500 1.5119 0.02611 0.02201 -0.0462 0.3123 1.0000
9.750 1.5324 0.02619 0.02212 -0.0451 0.3117 1.0000
10.000 1.5658 0.02516 0.02101 -0.0457 0.3107 1.0000
10.250 1.5806 0.02576 0.02167 -0.0439 0.3103 1.0000
10.500 1.6075 0.02530 0.02120 -0.0437 0.3098 1.0000
10.750 1.6332 0.02500 0.02089 -0.0433 0.3092 1.0000
11.000 1.6655 0.02410 0.01992 -0.0438 0.3085 1.0000
11.250 1.6759 0.02506 0.02098 -0.0415 0.3084 1.0000
11.500 1.7058 0.02441 0.02029 -0.0417 0.3078 1.0000
11.750 1.7331 0.02397 0.01983 -0.0416 0.3073 1.0000
12.000 1.7773 0.02205 0.01773 -0.0437 0.3061 1.0000
12.250 1.7994 0.02228 0.01795 -0.0431 0.3047 1.0000
12.500 1.8251 0.02115 0.01685 -0.0424 0.3037 1.0000
12.750 1.8438 0.02099 0.01676 -0.0409 0.3027 1.0000
13.000 1.8597 0.02127 0.01713 -0.0393 0.3021 1.0000
13.250 1.8895 0.01987 0.01572 -0.0391 0.2990 1.0000
13.500 1.9268 0.01790 0.01366 -0.0400 0.2954 1.0000
13.750 1.9492 0.01761 0.01339 -0.0392 0.2943 1.0000
14.000 1.9725 0.01715 0.01297 -0.0384 0.2919 1.0000
14.250 1.9878 0.01762 0.01356 -0.0368 0.2897 1.0000
14.500 2.0094 0.01752 0.01355 -0.0361 0.2819 1.0000
14.750 2.0350 0.01623 0.01196 -0.0353 0.2562 1.0000
15.000 2.0345 0.01691 0.01262 -0.0309 0.2465 1.0000
15.250 2.0028 0.01843 0.01409 -0.0215 0.2288 1.0000
15.500 1.9797 0.02002 0.01570 -0.0145 0.2178 1.0000
15.750 1.9208 0.02387 0.01958 -0.0056 0.2015 1.0000
16.000 1.9208 0.02529 0.02113 -0.0040 0.2034 1.0000
16.250 1.8708 0.03272 0.02884 -0.0050 0.2051 1.0000
16.500 1.7355 0.05120 0.04794 -0.0080 0.2261 1.0000
16.750 1.4696 0.08346 0.08056 -0.0131 0.2328 1.0000
17.000 1.4703 0.08587 0.08299 -0.0134 0.2307 1.0000
17.250 1.4594 0.08974 0.08679 -0.0141 0.2197 1.0000
17.500 1.4474 0.09380 0.09075 -0.0148 0.2060 1.0000
17.750 1.4463 0.09653 0.09347 -0.0153 0.2005 1.0000
18.000 1.4370 0.10033 0.09722 -0.0160 0.1915 1.0000
18.250 1.4354 0.10321 0.10010 -0.0166 0.1866 1.0000
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