CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YS AIRFOIL (clarkys-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.25 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkys-il-1000000-n5.txt Download as CSV file: xf-clarkys-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.3442 0.04086 0.03745 -0.0479 0.8170 0.0102
-16.750 -1.3581 0.03800 0.03442 -0.0459 0.8119 0.0103
-16.500 -1.3660 0.03581 0.03206 -0.0435 0.8081 0.0105
-16.250 -1.3708 0.03394 0.03005 -0.0408 0.8047 0.0107
-16.000 -1.3722 0.03236 0.02835 -0.0380 0.8012 0.0109
-15.750 -1.3701 0.03103 0.02691 -0.0353 0.7981 0.0113
-15.250 -1.3579 0.02892 0.02464 -0.0302 0.7932 0.0120
-15.000 -1.3497 0.02801 0.02364 -0.0277 0.7907 0.0124
-14.750 -1.3405 0.02717 0.02271 -0.0251 0.7882 0.0128
-14.500 -1.3309 0.02634 0.02179 -0.0225 0.7857 0.0131
-14.250 -1.3207 0.02557 0.02091 -0.0199 0.7834 0.0135
-14.000 -1.3099 0.02483 0.02004 -0.0172 0.7811 0.0137
-13.750 -1.2955 0.02426 0.01943 -0.0151 0.7791 0.0141
-13.500 -1.2774 0.02382 0.01896 -0.0136 0.7771 0.0146
-13.250 -1.2580 0.02342 0.01852 -0.0123 0.7749 0.0150
-13.000 -1.2388 0.02297 0.01802 -0.0109 0.7727 0.0154
-12.750 -1.2191 0.02254 0.01753 -0.0096 0.7706 0.0158
-12.500 -1.1994 0.02208 0.01699 -0.0083 0.7685 0.0162
-12.250 -1.1790 0.02165 0.01647 -0.0071 0.7665 0.0167
-12.000 -1.1582 0.02120 0.01594 -0.0059 0.7645 0.0171
-11.750 -1.1376 0.02069 0.01536 -0.0047 0.7624 0.0173
-11.500 -1.1172 0.02014 0.01473 -0.0035 0.7602 0.0176
-11.250 -1.0959 0.01967 0.01422 -0.0024 0.7578 0.0180
-11.000 -1.0731 0.01936 0.01387 -0.0015 0.7555 0.0183
-10.750 -1.0497 0.01912 0.01359 -0.0007 0.7533 0.0187
-10.500 -1.0264 0.01883 0.01326 0.0001 0.7512 0.0190
-10.250 -1.0025 0.01855 0.01296 0.0009 0.7489 0.0194
-10.000 -0.9793 0.01817 0.01252 0.0017 0.7465 0.0197
-9.750 -0.9559 0.01779 0.01208 0.0025 0.7439 0.0201
-9.500 -0.9317 0.01750 0.01173 0.0032 0.7413 0.0206
-9.250 -0.9078 0.01714 0.01130 0.0040 0.7388 0.0209
-9.000 -0.8838 0.01679 0.01088 0.0048 0.7365 0.0212
-8.750 -0.8590 0.01648 0.01051 0.0054 0.7339 0.0215
-8.500 -0.8342 0.01616 0.01014 0.0060 0.7310 0.0217
-8.250 -0.8092 0.01586 0.00979 0.0066 0.7280 0.0218
-8.000 -0.7869 0.01508 0.00892 0.0076 0.7251 0.0224
-7.750 -0.7630 0.01457 0.00836 0.0084 0.7222 0.0228
-7.500 -0.7382 0.01417 0.00792 0.0090 0.7194 0.0231
-7.250 -0.7129 0.01381 0.00753 0.0096 0.7160 0.0234
-7.000 -0.6873 0.01350 0.00719 0.0101 0.7122 0.0238
-6.750 -0.6618 0.01319 0.00684 0.0106 0.7086 0.0241
-6.500 -0.6362 0.01286 0.00646 0.0112 0.7054 0.0244
-6.250 -0.6104 0.01253 0.00610 0.0116 0.7015 0.0247
-6.000 -0.5844 0.01222 0.00575 0.0121 0.6965 0.0250
-5.750 -0.5586 0.01193 0.00540 0.0126 0.6908 0.0253
-5.500 -0.5323 0.01165 0.00509 0.0131 0.6847 0.0257
-5.250 -0.5061 0.01139 0.00478 0.0135 0.6778 0.0260
-5.000 -0.4797 0.01116 0.00451 0.0139 0.6713 0.0263
-4.750 -0.4531 0.01096 0.00427 0.0143 0.6640 0.0267
-4.500 -0.4266 0.01076 0.00402 0.0147 0.6570 0.0270
-4.250 -0.3999 0.01058 0.00380 0.0150 0.6492 0.0272
-4.000 -0.3733 0.01040 0.00357 0.0154 0.6415 0.0273
-3.750 -0.3469 0.01016 0.00329 0.0158 0.6317 0.0277
-3.500 -0.3203 0.00994 0.00303 0.0162 0.6224 0.0283
-3.000 -0.2668 0.00961 0.00263 0.0169 0.6048 0.0295
-2.750 -0.2400 0.00948 0.00247 0.0172 0.5974 0.0301
-2.500 -0.2130 0.00935 0.00232 0.0175 0.5899 0.0309
-2.000 -0.1590 0.00915 0.00207 0.0181 0.5722 0.0326
-1.750 -0.1320 0.00907 0.00196 0.0184 0.5639 0.0335
-1.500 -0.1049 0.00898 0.00186 0.0186 0.5555 0.0358
-1.250 -0.0781 0.00889 0.00177 0.0189 0.5473 0.0401
-1.000 -0.0518 0.00874 0.00169 0.0193 0.5382 0.0573
-0.750 -0.0253 0.00863 0.00162 0.0197 0.5293 0.0761
-0.500 0.0011 0.00855 0.00156 0.0200 0.5187 0.0916
-0.250 0.0273 0.00844 0.00151 0.0204 0.5069 0.1140
0.000 0.0529 0.00831 0.00147 0.0209 0.4953 0.1490
0.250 0.0782 0.00819 0.00144 0.0214 0.4832 0.1888
0.500 0.1031 0.00806 0.00143 0.0220 0.4701 0.2361
0.750 0.1281 0.00799 0.00142 0.0226 0.4555 0.2758
1.000 0.1525 0.00790 0.00143 0.0233 0.4398 0.3195
1.250 0.1719 0.00759 0.00142 0.0249 0.4237 0.4326
1.500 0.1597 0.00624 0.00120 0.0333 0.4125 0.7638
1.750 0.1773 0.00622 0.00142 0.0358 0.3949 0.8793
2.000 0.2033 0.00638 0.00153 0.0363 0.3776 0.8910
2.250 0.2291 0.00654 0.00165 0.0369 0.3638 0.9026
2.500 0.2558 0.00666 0.00174 0.0372 0.3539 0.9077
2.750 0.2815 0.00679 0.00181 0.0377 0.3453 0.9115
3.000 0.3089 0.00690 0.00191 0.0379 0.3377 0.9164
3.250 0.3367 0.00704 0.00202 0.0379 0.3286 0.9196
3.500 0.3636 0.00717 0.00210 0.0381 0.3193 0.9220
3.750 0.3902 0.00729 0.00220 0.0384 0.3120 0.9243
4.000 0.4162 0.00740 0.00228 0.0388 0.3050 0.9269
4.250 0.4413 0.00754 0.00238 0.0393 0.2967 0.9290
4.500 0.4682 0.00763 0.00245 0.0395 0.2911 0.9301
4.750 0.4955 0.00773 0.00253 0.0395 0.2855 0.9306
5.000 0.5228 0.00783 0.00262 0.0395 0.2795 0.9311
5.250 0.5500 0.00794 0.00271 0.0395 0.2719 0.9316
5.500 0.5769 0.00807 0.00282 0.0396 0.2661 0.9321
5.750 0.6042 0.00816 0.00292 0.0396 0.2610 0.9326
6.000 0.6308 0.00830 0.00304 0.0397 0.2539 0.9332
6.250 0.6575 0.00843 0.00316 0.0398 0.2462 0.9339
6.500 0.6834 0.00861 0.00331 0.0400 0.2351 0.9346
6.750 0.7086 0.00883 0.00347 0.0403 0.2201 0.9355
7.000 0.7315 0.00919 0.00371 0.0409 0.1931 0.9366
7.250 0.7538 0.00958 0.00398 0.0415 0.1693 0.9378
7.500 0.7751 0.01000 0.00430 0.0424 0.1475 0.9393
7.750 0.7953 0.01046 0.00464 0.0434 0.1243 0.9409
8.000 0.8160 0.01086 0.00496 0.0444 0.1078 0.9426
8.500 0.8591 0.01153 0.00556 0.0460 0.0877 0.9459
8.750 0.8824 0.01189 0.00589 0.0463 0.0795 0.9476
9.000 0.9055 0.01225 0.00624 0.0467 0.0733 0.9494
9.250 0.9286 0.01258 0.00657 0.0471 0.0677 0.9515
9.500 0.9498 0.01301 0.00698 0.0477 0.0601 0.9542
9.750 0.9694 0.01346 0.00740 0.0486 0.0515 0.9576
10.000 0.9807 0.01476 0.00849 0.0498 0.0190 0.9624
10.250 1.0035 0.01542 0.00916 0.0496 0.0153 0.9654
10.500 1.0268 0.01603 0.00981 0.0492 0.0134 0.9685
10.750 1.0490 0.01664 0.01046 0.0489 0.0125 0.9721
11.000 1.0749 0.01743 0.01130 0.0475 0.0114 0.9736
11.250 1.0999 0.01833 0.01224 0.0459 0.0105 0.9753
11.500 1.1236 0.01918 0.01314 0.0447 0.0100 0.9774
11.750 1.1448 0.02009 0.01410 0.0438 0.0096 0.9803
12.000 1.1620 0.02111 0.01516 0.0436 0.0090 0.9842
12.250 1.1820 0.02220 0.01630 0.0426 0.0086 0.9862
12.500 1.1993 0.02343 0.01757 0.0418 0.0082 0.9889
12.750 1.2143 0.02475 0.01895 0.0414 0.0078 0.9920
13.000 1.2290 0.02598 0.02025 0.0411 0.0076 0.9957
13.250 1.2452 0.02738 0.02171 0.0402 0.0075 0.9979
13.500 1.2610 0.02890 0.02329 0.0392 0.0072 0.9991
14.000 1.2805 0.03197 0.02646 0.0392 0.0068 1.0000
14.250 1.2798 0.03384 0.02841 0.0405 0.0068 1.0000
14.500 1.2820 0.03560 0.03021 0.0414 0.0065 1.0000
14.750 1.2825 0.03763 0.03230 0.0422 0.0063 1.0000
15.000 1.2817 0.03990 0.03464 0.0428 0.0062 1.0000
15.250 1.2813 0.04223 0.03704 0.0431 0.0062 1.0000
15.500 1.2772 0.04513 0.04002 0.0431 0.0059 1.0000
15.750 1.2720 0.04836 0.04333 0.0429 0.0058 1.0000
16.000 1.2703 0.05130 0.04636 0.0425 0.0057 1.0000
16.250 1.2659 0.05467 0.04981 0.0419 0.0057 1.0000
16.500 1.2639 0.05782 0.05305 0.0413 0.0056 1.0000
16.750 1.2576 0.06166 0.05698 0.0402 0.0056 1.0000
17.000 1.2498 0.06580 0.06122 0.0391 0.0056 1.0000
17.250 1.2431 0.06988 0.06538 0.0378 0.0055 1.0000
17.500 1.2380 0.07383 0.06942 0.0365 0.0054 1.0000
17.750 1.2264 0.07880 0.07450 0.0347 0.0054 1.0000
18.000 1.2168 0.08355 0.07934 0.0330 0.0054 1.0000
18.250 1.2073 0.08838 0.08427 0.0311 0.0053 1.0000
18.500 1.1956 0.09360 0.08959 0.0291 0.0052 1.0000
18.750 1.1811 0.09933 0.09542 0.0268 0.0053 1.0000
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