CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: CLARK YH AIRFOIL (clarkyh-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.13 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkyh-il-1000000-n5.txt Download as CSV file: xf-clarkyh-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YH 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
------ -------- --------- --------- -------- -------- --------
-17.750 -0.9024 0.12288 0.12074 0.0007 1.0000 0.0083
-17.500 -0.9591 0.10802 0.10574 -0.0085 1.0000 0.0082
-17.250 -1.2971 0.04101 0.03774 -0.0624 1.0000 0.0067
-17.000 -1.3122 0.03691 0.03346 -0.0632 1.0000 0.0067
-16.750 -1.3194 0.03424 0.03064 -0.0620 1.0000 0.0068
-16.500 -1.3214 0.03224 0.02851 -0.0600 1.0000 0.0069
-16.250 -1.3196 0.03061 0.02677 -0.0577 1.0000 0.0070
-16.000 -1.3145 0.02922 0.02526 -0.0553 1.0000 0.0071
-15.750 -1.3043 0.02794 0.02387 -0.0534 1.0000 0.0073
-15.500 -1.2915 0.02677 0.02260 -0.0518 1.0000 0.0074
-15.250 -1.2767 0.02571 0.02142 -0.0502 1.0000 0.0076
-15.000 -1.2613 0.02463 0.02024 -0.0487 1.0000 0.0077
-14.750 -1.2455 0.02352 0.01903 -0.0472 1.0000 0.0080
-14.500 -1.2278 0.02255 0.01798 -0.0459 1.0000 0.0083
-14.250 -1.2088 0.02169 0.01704 -0.0446 1.0000 0.0086
-14.000 -1.1887 0.02090 0.01619 -0.0434 1.0000 0.0089
-13.750 -1.1678 0.02018 0.01539 -0.0423 1.0000 0.0092
-13.500 -1.1407 0.01949 0.01460 -0.0424 0.9616 0.0095
-13.250 -1.1201 0.01887 0.01385 -0.0410 0.9350 0.0098
-13.000 -1.1004 0.01822 0.01308 -0.0394 0.9174 0.0103
-12.750 -1.0790 0.01763 0.01240 -0.0382 0.9056 0.0107
-12.250 -1.0333 0.01660 0.01119 -0.0360 0.8885 0.0117
-12.000 -1.0098 0.01612 0.01062 -0.0350 0.8810 0.0123
-11.750 -0.9864 0.01557 0.01001 -0.0341 0.8739 0.0131
-11.500 -0.9625 0.01511 0.00946 -0.0332 0.8659 0.0140
-11.250 -0.9378 0.01471 0.00898 -0.0323 0.8587 0.0148
-11.000 -0.9134 0.01423 0.00845 -0.0315 0.8516 0.0161
-10.750 -0.8885 0.01382 0.00799 -0.0307 0.8455 0.0175
-10.500 -0.8630 0.01344 0.00755 -0.0300 0.8393 0.0190
-10.250 -0.8378 0.01305 0.00713 -0.0293 0.8331 0.0211
-10.000 -0.8119 0.01271 0.00676 -0.0287 0.8279 0.0237
-9.750 -0.7856 0.01241 0.00646 -0.0282 0.8225 0.0270
-9.500 -0.7591 0.01219 0.00623 -0.0276 0.8165 0.0300
-9.250 -0.7320 0.01200 0.00604 -0.0272 0.8111 0.0326
-9.000 -0.7049 0.01182 0.00581 -0.0267 0.8058 0.0341
-8.750 -0.6779 0.01162 0.00558 -0.0263 0.8008 0.0358
-8.500 -0.6505 0.01145 0.00541 -0.0259 0.7952 0.0374
-8.250 -0.6231 0.01130 0.00524 -0.0255 0.7876 0.0389
-8.000 -0.5957 0.01117 0.00506 -0.0251 0.7797 0.0402
-7.750 -0.5682 0.01104 0.00488 -0.0248 0.7702 0.0413
-7.500 -0.5406 0.01091 0.00470 -0.0244 0.7613 0.0420
-7.250 -0.5129 0.01081 0.00455 -0.0241 0.7512 0.0425
-7.000 -0.4858 0.01060 0.00428 -0.0237 0.7394 0.0434
-6.750 -0.4592 0.01034 0.00396 -0.0232 0.7236 0.0450
-6.500 -0.4323 0.01019 0.00373 -0.0228 0.7014 0.0461
-6.250 -0.4053 0.01008 0.00352 -0.0224 0.6760 0.0471
-5.750 -0.3510 0.00987 0.00313 -0.0217 0.6413 0.0485
-5.500 -0.3236 0.00976 0.00295 -0.0214 0.6294 0.0491
-5.250 -0.2961 0.00967 0.00280 -0.0211 0.6170 0.0497
-5.000 -0.2686 0.00959 0.00265 -0.0209 0.6049 0.0504
-4.750 -0.2410 0.00950 0.00251 -0.0206 0.5938 0.0508
-4.500 -0.2133 0.00941 0.00237 -0.0204 0.5841 0.0511
-4.250 -0.1856 0.00933 0.00225 -0.0202 0.5747 0.0514
-4.000 -0.1577 0.00924 0.00213 -0.0200 0.5673 0.0517
-3.750 -0.1300 0.00916 0.00201 -0.0198 0.5581 0.0521
-3.500 -0.1023 0.00907 0.00189 -0.0197 0.5465 0.0532
-3.250 -0.0747 0.00902 0.00178 -0.0195 0.5310 0.0545
-3.000 -0.0472 0.00897 0.00168 -0.0193 0.5148 0.0561
-2.750 -0.0196 0.00894 0.00160 -0.0191 0.4990 0.0579
-2.500 0.0079 0.00891 0.00153 -0.0190 0.4842 0.0599
-2.250 0.0353 0.00887 0.00148 -0.0188 0.4712 0.0670
-2.000 0.0623 0.00879 0.00145 -0.0186 0.4599 0.0929
-1.750 0.0900 0.00876 0.00141 -0.0185 0.4506 0.0990
-1.500 0.1177 0.00876 0.00139 -0.0184 0.4420 0.1043
-1.250 0.1455 0.00876 0.00137 -0.0184 0.4335 0.1091
-1.000 0.1730 0.00875 0.00136 -0.0183 0.4249 0.1149
-0.750 0.2007 0.00874 0.00134 -0.0183 0.4180 0.1212
-0.250 0.2552 0.00860 0.00139 -0.0181 0.4073 0.1879
0.000 0.2831 0.00861 0.00141 -0.0181 0.4019 0.1930
0.250 0.3108 0.00865 0.00144 -0.0181 0.3944 0.1986
0.500 0.3387 0.00868 0.00147 -0.0181 0.3855 0.2028
0.750 0.3665 0.00874 0.00151 -0.0182 0.3771 0.2056
1.000 0.3941 0.00878 0.00155 -0.0182 0.3662 0.2108
1.250 0.4215 0.00884 0.00159 -0.0182 0.3528 0.2173
1.750 0.4706 0.00966 0.00195 -0.0176 0.2344 0.2291
2.250 0.5235 0.00987 0.00219 -0.0174 0.2125 0.2650
2.500 0.5454 0.00940 0.00230 -0.0167 0.2076 0.4838
2.750 0.5569 0.00838 0.00238 -0.0134 0.2050 0.8395
3.000 0.5824 0.00838 0.00250 -0.0130 0.2014 0.8783
3.250 0.6109 0.00843 0.00266 -0.0133 0.1976 0.9145
3.500 0.6560 0.00862 0.00291 -0.0173 0.1929 0.9488
3.750 0.6974 0.00880 0.00311 -0.0205 0.1899 0.9661
4.250 0.7586 0.00911 0.00342 -0.0222 0.1836 0.9783
4.500 0.7854 0.00933 0.00360 -0.0223 0.1769 0.9837
4.750 0.8208 0.00951 0.00377 -0.0243 0.1698 0.9865
5.000 0.8566 0.00976 0.00397 -0.0265 0.1607 0.9902
5.250 0.8886 0.00997 0.00416 -0.0279 0.1519 0.9931
5.500 0.9192 0.01032 0.00440 -0.0291 0.1331 0.9946
5.750 0.9479 0.01117 0.00497 -0.0303 0.0821 0.9963
6.000 0.9792 0.01154 0.00530 -0.0317 0.0739 0.9978
6.250 1.0100 0.01186 0.00561 -0.0330 0.0675 0.9990
6.500 1.0400 0.01222 0.00595 -0.0341 0.0598 1.0000
6.750 1.0589 0.01273 0.00635 -0.0329 0.0427 1.0000
7.000 1.0764 0.01332 0.00685 -0.0315 0.0275 1.0000
7.250 1.0957 0.01374 0.00725 -0.0304 0.0231 1.0000
7.500 1.1156 0.01409 0.00761 -0.0294 0.0209 1.0000
7.750 1.1342 0.01452 0.00804 -0.0282 0.0186 1.0000
8.000 1.1534 0.01488 0.00842 -0.0270 0.0172 1.0000
8.250 1.1718 0.01529 0.00883 -0.0258 0.0158 1.0000
8.500 1.1890 0.01574 0.00930 -0.0244 0.0145 1.0000
8.750 1.2069 0.01614 0.00972 -0.0232 0.0138 1.0000
9.000 1.2240 0.01656 0.01017 -0.0218 0.0131 1.0000
9.250 1.2400 0.01703 0.01066 -0.0203 0.0123 1.0000
9.500 1.2542 0.01757 0.01121 -0.0186 0.0115 1.0000
9.750 1.2690 0.01804 0.01172 -0.0169 0.0110 1.0000
10.000 1.2804 0.01853 0.01225 -0.0147 0.0106 1.0000
10.250 1.2914 0.01910 0.01286 -0.0126 0.0101 1.0000
10.500 1.3031 0.01977 0.01356 -0.0109 0.0097 1.0000
10.750 1.3146 0.02055 0.01439 -0.0095 0.0093 1.0000
11.000 1.3257 0.02145 0.01533 -0.0082 0.0090 1.0000
11.250 1.3382 0.02232 0.01625 -0.0072 0.0087 1.0000
11.500 1.3502 0.02328 0.01727 -0.0063 0.0085 1.0000
11.750 1.3615 0.02434 0.01838 -0.0055 0.0082 1.0000
12.000 1.3722 0.02549 0.01958 -0.0047 0.0079 1.0000
12.250 1.3820 0.02675 0.02090 -0.0041 0.0077 1.0000
12.500 1.3907 0.02816 0.02237 -0.0035 0.0074 1.0000
12.750 1.3976 0.02977 0.02404 -0.0029 0.0072 1.0000
13.000 1.4030 0.03161 0.02594 -0.0024 0.0070 1.0000
13.250 1.4095 0.03338 0.02779 -0.0022 0.0069 1.0000
13.500 1.4151 0.03534 0.02982 -0.0021 0.0067 1.0000
13.750 1.4194 0.03749 0.03205 -0.0021 0.0066 1.0000
14.000 1.4227 0.03982 0.03446 -0.0022 0.0065 1.0000
14.250 1.4248 0.04235 0.03708 -0.0025 0.0063 1.0000
14.500 1.4258 0.04506 0.03987 -0.0028 0.0062 1.0000
14.750 1.4254 0.04793 0.04283 -0.0032 0.0061 1.0000
15.000 1.4239 0.05105 0.04604 -0.0038 0.0060 1.0000
15.250 1.4213 0.05439 0.04947 -0.0045 0.0059 1.0000
15.500 1.4175 0.05793 0.05309 -0.0053 0.0059 1.0000
15.750 1.4125 0.06174 0.05699 -0.0063 0.0058 1.0000
16.000 1.4061 0.06584 0.06119 -0.0075 0.0057 1.0000
16.250 1.3985 0.07014 0.06558 -0.0087 0.0056 1.0000
16.500 1.3894 0.07476 0.07030 -0.0101 0.0056 1.0000
16.750 1.3788 0.07970 0.07533 -0.0117 0.0055 1.0000
17.000 1.3665 0.08492 0.08066 -0.0133 0.0055 1.0000
17.250 1.3531 0.09043 0.08628 -0.0152 0.0054 1.0000
17.500 1.3386 0.09623 0.09219 -0.0172 0.0054 1.0000
17.750 1.3228 0.10233 0.09839 -0.0194 0.0053 1.0000
|
Polar data table (+)
Polar graphs
<< Back to CLARK YH AIRFOIL (clarkyh-il)