CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK W AIRFOIL (clarkw-il) Reynolds number: 1,000,000 Max Cl/Cd: 116.12 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkw-il-1000000.txt Download as CSV file: xf-clarkw-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK W 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4108 0.12781 0.12597 -0.0310 1.0000 0.0224
-12.250 -0.4251 0.11833 0.11650 -0.0361 1.0000 0.0239
-12.000 -0.8416 0.03967 0.03725 -0.0780 0.9994 0.0213
-11.750 -0.8231 0.03687 0.03429 -0.0813 0.9970 0.0215
-11.500 -0.8036 0.03411 0.03134 -0.0842 0.9948 0.0218
-11.250 -0.7837 0.03161 0.02863 -0.0863 0.9926 0.0221
-11.000 -0.7640 0.02934 0.02614 -0.0875 0.9893 0.0225
-10.750 -0.7405 0.02733 0.02390 -0.0890 0.9869 0.0229
-10.500 -0.7131 0.02591 0.02228 -0.0905 0.9853 0.0233
-10.250 -0.6827 0.02501 0.02120 -0.0921 0.9841 0.0237
-10.000 -0.6507 0.02441 0.02046 -0.0937 0.9832 0.0239
-9.750 -0.6367 0.02087 0.01658 -0.0934 0.9784 0.0244
-9.500 -0.6105 0.01953 0.01515 -0.0940 0.9755 0.0248
-9.250 -0.5817 0.01861 0.01415 -0.0948 0.9731 0.0251
-9.000 -0.5527 0.01784 0.01331 -0.0955 0.9708 0.0255
-8.750 -0.5286 0.01727 0.01268 -0.0950 0.9658 0.0259
-8.500 -0.5031 0.01662 0.01196 -0.0948 0.9611 0.0263
-8.250 -0.4768 0.01590 0.01114 -0.0947 0.9573 0.0267
-8.000 -0.4529 0.01525 0.01041 -0.0940 0.9516 0.0270
-7.750 -0.4283 0.01464 0.00971 -0.0934 0.9459 0.0273
-7.500 -0.4021 0.01407 0.00905 -0.0931 0.9413 0.0277
-7.250 -0.3776 0.01360 0.00851 -0.0924 0.9348 0.0280
-7.000 -0.3517 0.01318 0.00801 -0.0920 0.9290 0.0282
-6.750 -0.3251 0.01287 0.00764 -0.0916 0.9234 0.0285
-6.500 -0.3016 0.01199 0.00668 -0.0909 0.9164 0.0290
-6.250 -0.2764 0.01133 0.00595 -0.0904 0.9104 0.0294
-6.000 -0.2510 0.01086 0.00546 -0.0899 0.9037 0.0299
-5.750 -0.2248 0.01048 0.00503 -0.0895 0.8970 0.0303
-5.500 -0.1983 0.01016 0.00466 -0.0892 0.8905 0.0307
-5.250 -0.1719 0.00985 0.00431 -0.0888 0.8827 0.0312
-5.000 -0.1453 0.00958 0.00399 -0.0884 0.8740 0.0317
-4.750 -0.1188 0.00934 0.00368 -0.0880 0.8643 0.0323
-4.500 -0.0919 0.00911 0.00341 -0.0876 0.8556 0.0329
-4.250 -0.0648 0.00894 0.00317 -0.0873 0.8477 0.0335
-4.000 -0.0376 0.00875 0.00295 -0.0871 0.8398 0.0340
-3.750 -0.0109 0.00847 0.00260 -0.0867 0.8319 0.0351
-3.500 0.0163 0.00827 0.00238 -0.0864 0.8240 0.0363
-3.250 0.0435 0.00812 0.00219 -0.0862 0.8161 0.0376
-3.000 0.0710 0.00798 0.00203 -0.0859 0.8082 0.0391
-2.750 0.0983 0.00786 0.00187 -0.0857 0.8001 0.0415
-2.500 0.1254 0.00767 0.00171 -0.0854 0.7922 0.0515
-2.250 0.1517 0.00739 0.00160 -0.0850 0.7837 0.0931
-2.000 0.1788 0.00726 0.00152 -0.0848 0.7754 0.1142
-1.750 0.2056 0.00713 0.00144 -0.0845 0.7665 0.1370
-1.500 0.2327 0.00699 0.00139 -0.0843 0.7574 0.1639
-1.250 0.2592 0.00688 0.00134 -0.0840 0.7480 0.1970
-1.000 0.2862 0.00678 0.00132 -0.0837 0.7379 0.2275
-0.750 0.3132 0.00671 0.00130 -0.0834 0.7276 0.2543
-0.500 0.3400 0.00669 0.00129 -0.0831 0.7165 0.2776
-0.250 0.3671 0.00665 0.00130 -0.0828 0.7047 0.3008
0.000 0.3941 0.00664 0.00130 -0.0826 0.6924 0.3206
0.250 0.4209 0.00666 0.00131 -0.0823 0.6795 0.3379
0.500 0.4476 0.00668 0.00133 -0.0819 0.6654 0.3561
0.750 0.4741 0.00671 0.00135 -0.0816 0.6509 0.3747
1.000 0.5005 0.00674 0.00137 -0.0812 0.6355 0.3922
1.250 0.5268 0.00676 0.00140 -0.0808 0.6186 0.4128
1.500 0.5525 0.00676 0.00144 -0.0803 0.6006 0.4468
1.750 0.5651 0.00574 0.00154 -0.0772 0.5844 0.8531
2.000 0.5916 0.00576 0.00173 -0.0764 0.5652 0.9564
2.250 0.6271 0.00597 0.00185 -0.0780 0.5420 0.9769
2.500 0.6640 0.00620 0.00196 -0.0799 0.5177 0.9856
2.750 0.7023 0.00644 0.00207 -0.0823 0.4927 0.9910
3.000 0.7402 0.00667 0.00219 -0.0846 0.4681 0.9950
3.250 0.7789 0.00690 0.00230 -0.0871 0.4456 0.9980
3.500 0.8138 0.00712 0.00242 -0.0887 0.4261 1.0000
4.000 0.8588 0.00745 0.00263 -0.0865 0.3974 1.0000
4.250 0.8813 0.00761 0.00275 -0.0854 0.3852 1.0000
4.500 0.9034 0.00778 0.00287 -0.0843 0.3727 1.0000
4.750 0.9251 0.00798 0.00300 -0.0830 0.3579 1.0000
5.000 0.9468 0.00818 0.00314 -0.0818 0.3439 1.0000
5.250 0.9683 0.00839 0.00328 -0.0805 0.3291 1.0000
5.750 1.0125 0.00877 0.00358 -0.0782 0.3042 1.0000
6.000 1.0346 0.00897 0.00374 -0.0770 0.2930 1.0000
6.250 1.0565 0.00920 0.00392 -0.0759 0.2807 1.0000
6.500 1.0786 0.00944 0.00411 -0.0748 0.2681 1.0000
6.750 1.1009 0.00969 0.00431 -0.0737 0.2541 1.0000
7.000 1.1227 0.00998 0.00454 -0.0726 0.2379 1.0000
7.250 1.1444 0.01031 0.00479 -0.0716 0.2198 1.0000
7.500 1.1648 0.01072 0.00509 -0.0703 0.1959 1.0000
7.750 1.1831 0.01130 0.00548 -0.0687 0.1640 1.0000
8.000 1.2000 0.01198 0.00596 -0.0670 0.1305 1.0000
8.250 1.2182 0.01257 0.00643 -0.0654 0.1098 1.0000
8.500 1.2376 0.01308 0.00685 -0.0641 0.0942 1.0000
8.750 1.2559 0.01365 0.00732 -0.0626 0.0762 1.0000
9.000 1.2730 0.01427 0.00783 -0.0609 0.0600 1.0000
9.250 1.2902 0.01482 0.00833 -0.0592 0.0504 1.0000
9.500 1.3066 0.01536 0.00883 -0.0574 0.0443 1.0000
9.750 1.3243 0.01582 0.00929 -0.0558 0.0408 1.0000
10.000 1.3402 0.01640 0.00986 -0.0539 0.0374 1.0000
10.250 1.3584 0.01683 0.01033 -0.0525 0.0356 1.0000
10.500 1.3746 0.01739 0.01090 -0.0508 0.0336 1.0000
10.750 1.3890 0.01807 0.01159 -0.0489 0.0313 1.0000
11.000 1.4065 0.01855 0.01212 -0.0475 0.0301 1.0000
11.250 1.4220 0.01915 0.01275 -0.0459 0.0286 1.0000
11.500 1.4348 0.01995 0.01356 -0.0440 0.0270 1.0000
11.750 1.4485 0.02069 0.01435 -0.0423 0.0258 1.0000
12.000 1.4637 0.02134 0.01505 -0.0408 0.0249 1.0000
12.250 1.4774 0.02211 0.01585 -0.0393 0.0238 1.0000
12.500 1.4883 0.02308 0.01685 -0.0375 0.0226 1.0000
12.750 1.4977 0.02419 0.01802 -0.0357 0.0216 1.0000
13.000 1.5111 0.02504 0.01892 -0.0343 0.0209 1.0000
13.250 1.5230 0.02602 0.01995 -0.0329 0.0202 1.0000
13.500 1.5333 0.02715 0.02112 -0.0315 0.0194 1.0000
13.750 1.5404 0.02855 0.02257 -0.0299 0.0187 1.0000
14.000 1.5425 0.03042 0.02452 -0.0281 0.0180 1.0000
14.250 1.5524 0.03171 0.02587 -0.0270 0.0176 1.0000
14.500 1.5602 0.03320 0.02744 -0.0259 0.0172 1.0000
14.750 1.5671 0.03482 0.02912 -0.0248 0.0167 1.0000
15.000 1.5731 0.03657 0.03094 -0.0239 0.0162 1.0000
15.250 1.5770 0.03856 0.03300 -0.0229 0.0158 1.0000
15.500 1.5775 0.04096 0.03546 -0.0221 0.0153 1.0000
15.750 1.5715 0.04418 0.03878 -0.0213 0.0149 1.0000
16.000 1.5709 0.04696 0.04164 -0.0209 0.0146 1.0000
16.250 1.5729 0.04951 0.04429 -0.0206 0.0144 1.0000
16.500 1.5728 0.05242 0.04729 -0.0206 0.0142 1.0000
16.750 1.5712 0.05560 0.05056 -0.0207 0.0139 1.0000
17.000 1.5684 0.05900 0.05406 -0.0210 0.0137 1.0000
17.250 1.5639 0.06271 0.05787 -0.0215 0.0135 1.0000
17.500 1.5586 0.06665 0.06191 -0.0221 0.0132 1.0000
17.750 1.5523 0.07081 0.06616 -0.0230 0.0131 1.0000
18.000 1.5438 0.07534 0.07080 -0.0241 0.0129 1.0000
18.250 1.5336 0.08019 0.07574 -0.0253 0.0127 1.0000
18.500 1.5217 0.08541 0.08106 -0.0269 0.0126 1.0000
18.750 1.5080 0.09096 0.08672 -0.0286 0.0124 1.0000
19.000 1.4926 0.09681 0.09267 -0.0305 0.0123 1.0000
19.250 1.4765 0.10285 0.09881 -0.0326 0.0122 1.0000
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