CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YS AIRFOIL (clarkys-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.68 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkys-il-1000000.txt Download as CSV file: xf-clarkys-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -1.0722 0.03586 0.03233 -0.0323 0.8130 0.0177
-12.750 -1.0712 0.03466 0.03098 -0.0290 0.8098 0.0178
-12.500 -1.0910 0.03195 0.02799 -0.0230 0.8063 0.0181
-12.250 -1.0955 0.03018 0.02604 -0.0186 0.8030 0.0183
-12.000 -1.0826 0.02948 0.02529 -0.0165 0.8002 0.0186
-11.750 -1.0657 0.02907 0.02487 -0.0149 0.7977 0.0188
-11.500 -1.0490 0.02860 0.02434 -0.0133 0.7949 0.0191
-11.250 -1.0297 0.02840 0.02411 -0.0120 0.7922 0.0194
-11.000 -1.0121 0.02792 0.02356 -0.0104 0.7896 0.0197
-10.750 -0.9945 0.02737 0.02291 -0.0089 0.7867 0.0201
-10.500 -0.9777 0.02656 0.02199 -0.0072 0.7845 0.0205
-10.250 -0.9609 0.02565 0.02094 -0.0055 0.7818 0.0210
-10.000 -0.9427 0.02488 0.02003 -0.0040 0.7790 0.0213
-9.750 -0.9231 0.02430 0.01932 -0.0025 0.7763 0.0216
-9.500 -0.9010 0.02427 0.01918 -0.0014 0.7737 0.0219
-9.250 -0.8906 0.02144 0.01610 0.0009 0.7712 0.0227
-9.000 -0.8686 0.02088 0.01552 0.0019 0.7687 0.0231
-8.750 -0.8463 0.02033 0.01491 0.0028 0.7658 0.0234
-8.500 -0.8237 0.01979 0.01430 0.0038 0.7630 0.0239
-8.250 -0.8008 0.01921 0.01364 0.0047 0.7604 0.0243
-8.000 -0.7776 0.01866 0.01299 0.0056 0.7576 0.0248
-7.750 -0.7536 0.01819 0.01245 0.0063 0.7549 0.0254
-7.500 -0.7292 0.01771 0.01190 0.0071 0.7520 0.0258
-7.250 -0.7046 0.01725 0.01135 0.0078 0.7488 0.0262
-7.000 -0.6797 0.01686 0.01087 0.0085 0.7458 0.0264
-6.750 -0.6551 0.01612 0.01002 0.0091 0.7430 0.0267
-6.500 -0.6314 0.01470 0.00852 0.0098 0.7401 0.0276
-6.250 -0.6061 0.01415 0.00796 0.0103 0.7367 0.0281
-6.000 -0.5806 0.01367 0.00746 0.0109 0.7331 0.0286
-5.750 -0.5549 0.01324 0.00699 0.0114 0.7292 0.0291
-5.500 -0.5292 0.01284 0.00653 0.0120 0.7250 0.0295
-5.250 -0.5031 0.01244 0.00611 0.0124 0.7206 0.0301
-5.000 -0.4771 0.01205 0.00569 0.0129 0.7157 0.0306
-4.750 -0.4510 0.01174 0.00534 0.0134 0.7112 0.0312
-4.500 -0.4245 0.01145 0.00502 0.0139 0.7066 0.0316
-4.250 -0.3980 0.01117 0.00471 0.0143 0.7010 0.0320
-4.000 -0.3716 0.01091 0.00440 0.0147 0.6955 0.0322
-3.750 -0.3465 0.01037 0.00382 0.0154 0.6895 0.0331
-3.500 -0.3204 0.01003 0.00345 0.0159 0.6827 0.0341
-3.250 -0.2939 0.00979 0.00318 0.0163 0.6767 0.0350
-3.000 -0.2670 0.00958 0.00296 0.0167 0.6704 0.0360
-2.750 -0.2403 0.00940 0.00274 0.0171 0.6640 0.0371
-2.500 -0.2132 0.00924 0.00257 0.0174 0.6573 0.0383
-2.250 -0.1864 0.00908 0.00237 0.0177 0.6500 0.0399
-2.000 -0.1597 0.00889 0.00219 0.0181 0.6435 0.0436
-1.750 -0.1329 0.00873 0.00205 0.0185 0.6363 0.0503
-1.500 -0.1071 0.00848 0.00192 0.0190 0.6294 0.0816
-1.250 -0.0812 0.00825 0.00181 0.0195 0.6219 0.1127
-1.000 -0.0562 0.00801 0.00172 0.0201 0.6144 0.1590
-0.750 -0.0314 0.00774 0.00164 0.0207 0.6060 0.2173
-0.500 -0.0071 0.00751 0.00159 0.0215 0.5979 0.2752
-0.250 0.0170 0.00728 0.00154 0.0223 0.5895 0.3332
0.000 0.0366 0.00688 0.00147 0.0239 0.5818 0.4400
0.250 0.0362 0.00584 0.00127 0.0298 0.5744 0.6838
0.500 0.0414 0.00536 0.00139 0.0352 0.5670 0.8780
0.750 0.0668 0.00544 0.00145 0.0360 0.5577 0.8933
1.000 0.0951 0.00556 0.00156 0.0362 0.5481 0.9044
1.500 0.1499 0.00587 0.00181 0.0370 0.5251 0.9221
1.750 0.1805 0.00608 0.00199 0.0368 0.5122 0.9296
2.000 0.2133 0.00635 0.00222 0.0360 0.4981 0.9352
2.250 0.2361 0.00652 0.00232 0.0373 0.4837 0.9399
2.500 0.2730 0.00679 0.00253 0.0356 0.4647 0.9432
2.750 0.3105 0.00711 0.00275 0.0336 0.4423 0.9449
3.000 0.3449 0.00739 0.00293 0.0322 0.4161 0.9462
3.250 0.3772 0.00766 0.00308 0.0312 0.3911 0.9475
3.500 0.4097 0.00792 0.00325 0.0301 0.3718 0.9488
3.750 0.4412 0.00815 0.00341 0.0293 0.3563 0.9503
4.000 0.4580 0.00825 0.00347 0.0317 0.3468 0.9534
4.250 0.4702 0.00825 0.00344 0.0350 0.3384 0.9559
4.500 0.4972 0.00833 0.00348 0.0350 0.3293 0.9563
4.750 0.5230 0.00839 0.00351 0.0353 0.3220 0.9567
5.000 0.5490 0.00846 0.00356 0.0355 0.3159 0.9571
5.250 0.5756 0.00850 0.00361 0.0357 0.3107 0.9575
5.500 0.6019 0.00860 0.00369 0.0359 0.3043 0.9579
5.750 0.6285 0.00868 0.00376 0.0360 0.2988 0.9583
6.000 0.6554 0.00875 0.00384 0.0360 0.2935 0.9588
6.250 0.6817 0.00887 0.00395 0.0361 0.2874 0.9593
6.500 0.7087 0.00895 0.00404 0.0362 0.2815 0.9598
6.750 0.7348 0.00910 0.00416 0.0363 0.2716 0.9604
7.000 0.7614 0.00920 0.00426 0.0363 0.2625 0.9611
7.250 0.7871 0.00935 0.00439 0.0365 0.2525 0.9619
7.500 0.8121 0.00954 0.00453 0.0368 0.2393 0.9628
7.750 0.8362 0.00976 0.00470 0.0373 0.2220 0.9639
8.000 0.8570 0.01012 0.00494 0.0382 0.1963 0.9656
8.250 0.8735 0.01051 0.00521 0.0400 0.1716 0.9679
8.500 0.8895 0.01093 0.00553 0.0419 0.1500 0.9702
8.750 0.9148 0.01144 0.00593 0.0416 0.1288 0.9711
9.000 0.9408 0.01193 0.00634 0.0412 0.1124 0.9719
9.250 0.9672 0.01240 0.00675 0.0407 0.0993 0.9726
9.500 0.9940 0.01288 0.00718 0.0401 0.0890 0.9733
9.750 1.0210 0.01330 0.00760 0.0395 0.0810 0.9741
10.000 1.0469 0.01378 0.00804 0.0391 0.0732 0.9750
10.250 1.0712 0.01433 0.00854 0.0388 0.0639 0.9764
10.500 1.0912 0.01511 0.00921 0.0391 0.0464 0.9786
10.750 1.0962 0.01657 0.01048 0.0413 0.0203 0.9833
11.000 1.1181 0.01746 0.01140 0.0407 0.0171 0.9846
11.250 1.1404 0.01831 0.01230 0.0399 0.0159 0.9861
11.500 1.1605 0.01941 0.01346 0.0388 0.0148 0.9882
11.750 1.1784 0.02069 0.01481 0.0379 0.0139 0.9908
12.000 1.1956 0.02177 0.01596 0.0375 0.0134 0.9936
12.250 1.2164 0.02295 0.01721 0.0362 0.0130 0.9950
12.500 1.2355 0.02430 0.01862 0.0348 0.0125 0.9967
12.750 1.2515 0.02599 0.02037 0.0334 0.0119 0.9985
13.000 1.2662 0.02780 0.02226 0.0320 0.0117 0.9997
13.250 1.2501 0.02999 0.02454 0.0354 0.0112 1.0000
13.500 1.2418 0.03183 0.02645 0.0381 0.0112 1.0000
13.750 1.2435 0.03331 0.02798 0.0397 0.0110 1.0000
14.000 1.2428 0.03519 0.02993 0.0410 0.0109 1.0000
14.250 1.2427 0.03720 0.03202 0.0419 0.0108 1.0000
14.500 1.2406 0.03954 0.03443 0.0426 0.0106 1.0000
14.750 1.2393 0.04192 0.03689 0.0431 0.0104 1.0000
15.000 1.2369 0.04458 0.03962 0.0433 0.0102 1.0000
15.250 1.2344 0.04743 0.04255 0.0432 0.0101 1.0000
15.500 1.2335 0.05021 0.04541 0.0429 0.0099 1.0000
15.750 1.2291 0.05355 0.04882 0.0424 0.0097 1.0000
16.000 1.2215 0.05740 0.05277 0.0416 0.0096 1.0000
16.250 1.2175 0.06093 0.05637 0.0407 0.0095 1.0000
16.500 1.2089 0.06517 0.06070 0.0395 0.0095 1.0000
16.750 1.2000 0.06955 0.06516 0.0382 0.0093 1.0000
17.000 1.1910 0.07406 0.06975 0.0367 0.0092 1.0000
17.250 1.1813 0.07875 0.07454 0.0351 0.0092 1.0000
17.500 1.1688 0.08394 0.07981 0.0332 0.0090 1.0000
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