CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YS AIRFOIL (clarkys-il) Reynolds number: 500,000 Max Cl/Cd: 68.34 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkys-il-500000-n5.txt Download as CSV file: xf-clarkys-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YS AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9918 0.05341 0.05033 -0.0393 0.8304 0.0172
-14.000 -1.0282 0.04673 0.04337 -0.0416 0.8238 0.0171
-13.750 -1.0559 0.04234 0.03870 -0.0399 0.8190 0.0173
-13.500 -1.0743 0.03921 0.03529 -0.0368 0.8145 0.0174
-13.250 -1.0755 0.03772 0.03368 -0.0341 0.8106 0.0176
-13.000 -1.0709 0.03668 0.03256 -0.0317 0.8072 0.0178
-12.750 -1.0635 0.03586 0.03168 -0.0293 0.8039 0.0180
-12.500 -1.0517 0.03543 0.03121 -0.0272 0.8006 0.0182
-12.250 -1.0453 0.03456 0.03023 -0.0244 0.7975 0.0184
-12.000 -1.0345 0.03407 0.02966 -0.0220 0.7947 0.0188
-11.750 -1.0258 0.03313 0.02861 -0.0195 0.7919 0.0191
-11.500 -1.0146 0.03213 0.02747 -0.0174 0.7890 0.0195
-11.250 -1.0032 0.03101 0.02618 -0.0152 0.7861 0.0199
-11.000 -0.9914 0.02981 0.02476 -0.0130 0.7833 0.0204
-10.750 -0.9783 0.02862 0.02335 -0.0110 0.7809 0.0209
-10.500 -0.9625 0.02763 0.02216 -0.0093 0.7782 0.0214
-10.250 -0.9450 0.02679 0.02114 -0.0077 0.7753 0.0217
-10.000 -0.9296 0.02553 0.01969 -0.0060 0.7724 0.0222
-9.750 -0.9115 0.02462 0.01870 -0.0045 0.7697 0.0226
-9.500 -0.8911 0.02405 0.01806 -0.0034 0.7672 0.0230
-9.250 -0.8702 0.02348 0.01742 -0.0023 0.7645 0.0234
-9.000 -0.8486 0.02292 0.01678 -0.0013 0.7615 0.0239
-8.750 -0.8270 0.02222 0.01598 -0.0002 0.7584 0.0243
-8.500 -0.8050 0.02158 0.01521 0.0007 0.7555 0.0248
-8.250 -0.7825 0.02093 0.01444 0.0017 0.7529 0.0254
-8.000 -0.7595 0.02028 0.01366 0.0026 0.7502 0.0259
-7.750 -0.7360 0.01960 0.01287 0.0034 0.7470 0.0263
-7.500 -0.7120 0.01897 0.01214 0.0041 0.7436 0.0266
-7.250 -0.6876 0.01847 0.01152 0.0048 0.7406 0.0270
-7.000 -0.6629 0.01804 0.01098 0.0055 0.7377 0.0273
-6.750 -0.6386 0.01717 0.01002 0.0061 0.7345 0.0277
-6.500 -0.6142 0.01635 0.00914 0.0067 0.7309 0.0282
-6.250 -0.5893 0.01574 0.00847 0.0073 0.7273 0.0286
-6.000 -0.5642 0.01523 0.00791 0.0079 0.7239 0.0290
-5.750 -0.5389 0.01479 0.00742 0.0085 0.7207 0.0294
-5.500 -0.5132 0.01437 0.00698 0.0089 0.7165 0.0299
-5.250 -0.4873 0.01399 0.00657 0.0094 0.7123 0.0305
-5.000 -0.4615 0.01365 0.00617 0.0099 0.7079 0.0312
-4.750 -0.4356 0.01329 0.00578 0.0104 0.7023 0.0317
-4.500 -0.4096 0.01294 0.00539 0.0109 0.6960 0.0322
-4.250 -0.3836 0.01264 0.00502 0.0114 0.6905 0.0327
-4.000 -0.3572 0.01234 0.00470 0.0118 0.6839 0.0331
-3.750 -0.3310 0.01208 0.00438 0.0123 0.6774 0.0336
-3.500 -0.3045 0.01184 0.00410 0.0127 0.6702 0.0340
-3.250 -0.2782 0.01157 0.00379 0.0131 0.6627 0.0347
-3.000 -0.2518 0.01132 0.00351 0.0136 0.6548 0.0358
-2.750 -0.2253 0.01111 0.00326 0.0140 0.6458 0.0370
-2.500 -0.1987 0.01093 0.00306 0.0143 0.6376 0.0389
-2.250 -0.1721 0.01078 0.00288 0.0147 0.6301 0.0410
-2.000 -0.1454 0.01061 0.00271 0.0151 0.6231 0.0452
-1.750 -0.1191 0.01042 0.00257 0.0155 0.6155 0.0562
-1.500 -0.0927 0.01025 0.00245 0.0158 0.6079 0.0754
-1.250 -0.0664 0.01010 0.00233 0.0162 0.5991 0.0914
-1.000 -0.0404 0.00993 0.00223 0.0167 0.5907 0.1135
-0.750 -0.0151 0.00971 0.00214 0.0172 0.5817 0.1541
-0.500 0.0099 0.00948 0.00207 0.0177 0.5732 0.2044
-0.250 0.0350 0.00932 0.00202 0.0183 0.5645 0.2471
0.000 0.0594 0.00911 0.00197 0.0190 0.5551 0.3001
0.250 0.0811 0.00878 0.00192 0.0202 0.5461 0.3845
0.500 0.0928 0.00811 0.00182 0.0235 0.5363 0.5528
0.750 0.0981 0.00724 0.00204 0.0289 0.5272 0.8733
1.000 0.1223 0.00740 0.00215 0.0300 0.5150 0.8936
1.250 0.1508 0.00764 0.00235 0.0302 0.5022 0.9094
1.500 0.1837 0.00791 0.00258 0.0295 0.4882 0.9189
1.750 0.2137 0.00815 0.00276 0.0293 0.4735 0.9258
2.000 0.2390 0.00833 0.00286 0.0300 0.4583 0.9310
2.250 0.2810 0.00868 0.00312 0.0271 0.4389 0.9338
2.500 0.3148 0.00892 0.00327 0.0259 0.4190 0.9356
2.750 0.3467 0.00915 0.00341 0.0250 0.4002 0.9376
3.000 0.3760 0.00936 0.00355 0.0247 0.3855 0.9402
3.250 0.3827 0.00940 0.00354 0.0293 0.3761 0.9452
3.500 0.4165 0.00961 0.00369 0.0279 0.3641 0.9460
3.750 0.4436 0.00973 0.00377 0.0280 0.3527 0.9464
4.000 0.4691 0.00986 0.00384 0.0283 0.3418 0.9467
4.250 0.4947 0.00998 0.00392 0.0286 0.3326 0.9471
4.500 0.5206 0.01009 0.00400 0.0289 0.3246 0.9475
5.000 0.5721 0.01035 0.00421 0.0294 0.3074 0.9485
5.250 0.5976 0.01048 0.00432 0.0297 0.3005 0.9490
5.500 0.6234 0.01060 0.00444 0.0299 0.2941 0.9496
5.750 0.6490 0.01072 0.00457 0.0302 0.2868 0.9502
6.000 0.6743 0.01087 0.00471 0.0305 0.2806 0.9510
6.250 0.6998 0.01098 0.00484 0.0308 0.2745 0.9517
6.500 0.7243 0.01114 0.00500 0.0313 0.2677 0.9527
6.750 0.7489 0.01127 0.00515 0.0318 0.2599 0.9537
7.000 0.7719 0.01145 0.00532 0.0324 0.2502 0.9549
7.250 0.7936 0.01164 0.00549 0.0334 0.2375 0.9565
7.500 0.8112 0.01187 0.00567 0.0352 0.2199 0.9587
7.750 0.8327 0.01225 0.00594 0.0359 0.1952 0.9601
8.000 0.8560 0.01286 0.00639 0.0359 0.1648 0.9609
8.250 0.8799 0.01340 0.00684 0.0360 0.1433 0.9618
8.500 0.9031 0.01398 0.00733 0.0360 0.1234 0.9628
8.750 0.9263 0.01452 0.00781 0.0361 0.1083 0.9640
9.000 0.9496 0.01503 0.00828 0.0361 0.0969 0.9653
9.250 0.9725 0.01551 0.00876 0.0363 0.0889 0.9668
9.500 0.9929 0.01603 0.00926 0.0369 0.0812 0.9690
9.750 1.0085 0.01647 0.00972 0.0385 0.0751 0.9725
10.000 1.0335 0.01710 0.01034 0.0379 0.0669 0.9734
10.250 1.0567 0.01782 0.01105 0.0374 0.0579 0.9747
10.500 1.0734 0.01881 0.01195 0.0377 0.0413 0.9771
10.750 1.0775 0.02057 0.01357 0.0386 0.0194 0.9822
11.000 1.0932 0.02180 0.01484 0.0382 0.0164 0.9850
11.250 1.1117 0.02302 0.01612 0.0373 0.0150 0.9870
11.500 1.1282 0.02431 0.01749 0.0366 0.0138 0.9897
11.750 1.1447 0.02549 0.01876 0.0362 0.0132 0.9924
12.000 1.1598 0.02684 0.02019 0.0357 0.0125 0.9951
12.250 1.1757 0.02831 0.02175 0.0347 0.0119 0.9976
12.500 1.1897 0.03006 0.02358 0.0336 0.0113 0.9994
12.750 1.1907 0.03190 0.02549 0.0347 0.0107 1.0000
13.000 1.1868 0.03357 0.02723 0.0369 0.0105 1.0000
13.250 1.1846 0.03539 0.02912 0.0386 0.0104 1.0000
13.500 1.1847 0.03723 0.03105 0.0398 0.0102 1.0000
13.750 1.1840 0.03928 0.03318 0.0408 0.0100 1.0000
14.000 1.1829 0.04152 0.03550 0.0415 0.0099 1.0000
14.250 1.1806 0.04402 0.03809 0.0420 0.0097 1.0000
14.500 1.1778 0.04671 0.04087 0.0422 0.0094 1.0000
14.750 1.1750 0.04960 0.04384 0.0421 0.0093 1.0000
15.000 1.1702 0.05288 0.04722 0.0417 0.0092 1.0000
15.250 1.1667 0.05613 0.05056 0.0412 0.0090 1.0000
15.500 1.1610 0.05978 0.05431 0.0404 0.0088 1.0000
15.750 1.1545 0.06367 0.05829 0.0395 0.0087 1.0000
16.000 1.1484 0.06761 0.06232 0.0384 0.0085 1.0000
16.250 1.1404 0.07195 0.06675 0.0370 0.0085 1.0000
16.500 1.1316 0.07648 0.07140 0.0355 0.0084 1.0000
16.750 1.1211 0.08138 0.07638 0.0338 0.0082 1.0000
17.000 1.1118 0.08616 0.08127 0.0321 0.0082 1.0000
17.250 1.1017 0.09115 0.08634 0.0303 0.0082 1.0000
17.500 1.0899 0.09643 0.09171 0.0283 0.0080 1.0000
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