Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Davis AIRFOIL (davis-il) Reynolds number: 500,000 Max Cl/Cd: 101.36 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davis-il-500000.txt Download as CSV file: xf-davis-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Davis 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4145 0.09039 0.08830 -0.0382 1.0000 0.0240
-9.250 -0.5142 0.06096 0.05895 -0.0557 0.9959 0.0162
-9.000 -0.5364 0.04072 0.03803 -0.0816 0.9845 0.0154
-8.750 -0.5343 0.03429 0.03105 -0.0845 0.9770 0.0155
-8.500 -0.5170 0.02952 0.02572 -0.0868 0.9729 0.0157
-8.250 -0.4894 0.02656 0.02227 -0.0889 0.9709 0.0165
-8.000 -0.4722 0.02457 0.01993 -0.0878 0.9642 0.0167
-7.750 -0.4487 0.02121 0.01614 -0.0886 0.9608 0.0174
-7.500 -0.4169 0.01961 0.01442 -0.0902 0.9590 0.0181
-7.250 -0.3825 0.01853 0.01321 -0.0921 0.9577 0.0190
-7.000 -0.3533 0.01759 0.01215 -0.0926 0.9544 0.0200
-6.750 -0.3249 0.01691 0.01135 -0.0928 0.9496 0.0213
-6.500 -0.2921 0.01563 0.00989 -0.0941 0.9471 0.0228
-6.250 -0.2593 0.01449 0.00871 -0.0955 0.9448 0.0244
-6.000 -0.2238 0.01375 0.00791 -0.0972 0.9428 0.0263
-5.750 -0.2006 0.01327 0.00736 -0.0961 0.9352 0.0280
-5.500 -0.1704 0.01235 0.00634 -0.0967 0.9309 0.0304
-5.250 -0.1417 0.01164 0.00559 -0.0970 0.9257 0.0332
-5.000 -0.1155 0.01118 0.00506 -0.0965 0.9181 0.0360
-4.750 -0.0842 0.01063 0.00443 -0.0972 0.9134 0.0397
-4.500 -0.0609 0.01020 0.00397 -0.0962 0.9035 0.0446
-4.250 -0.0327 0.00981 0.00353 -0.0961 0.8955 0.0519
-4.000 -0.0069 0.00922 0.00313 -0.0957 0.8858 0.0940
-3.750 0.0182 0.00888 0.00294 -0.0951 0.8748 0.1445
-3.500 0.0454 0.00869 0.00275 -0.0950 0.8647 0.1671
-3.250 0.0732 0.00850 0.00257 -0.0949 0.8549 0.1874
-3.000 0.0993 0.00835 0.00246 -0.0945 0.8433 0.2110
-2.750 0.1257 0.00822 0.00234 -0.0941 0.8323 0.2355
-2.500 0.1524 0.00811 0.00222 -0.0938 0.8219 0.2590
-2.250 0.1789 0.00799 0.00211 -0.0935 0.8116 0.2818
-2.000 0.2044 0.00786 0.00202 -0.0930 0.8005 0.3090
-1.750 0.2298 0.00772 0.00197 -0.0924 0.7900 0.3499
-1.500 0.2551 0.00759 0.00193 -0.0919 0.7802 0.4003
-1.250 0.2801 0.00747 0.00190 -0.0913 0.7703 0.4497
-1.000 0.3048 0.00734 0.00188 -0.0906 0.7608 0.4965
-0.750 0.3289 0.00718 0.00185 -0.0898 0.7518 0.5537
-0.500 0.3483 0.00681 0.00186 -0.0880 0.7415 0.6747
-0.250 0.3670 0.00644 0.00196 -0.0856 0.7312 0.8375
0.000 0.4134 0.00643 0.00206 -0.0892 0.7204 0.9297
0.250 0.4620 0.00655 0.00210 -0.0935 0.7088 0.9586
0.500 0.5029 0.00665 0.00214 -0.0963 0.6974 0.9736
0.750 0.5447 0.00675 0.00218 -0.0993 0.6862 0.9856
1.000 0.5901 0.00684 0.00221 -0.1031 0.6744 0.9948
1.250 0.6314 0.00690 0.00221 -0.1061 0.6609 1.0000
1.500 0.6523 0.00696 0.00221 -0.1047 0.6462 1.0000
1.750 0.6732 0.00703 0.00223 -0.1033 0.6298 1.0000
2.000 0.6937 0.00713 0.00225 -0.1017 0.6119 1.0000
2.250 0.7140 0.00725 0.00229 -0.1001 0.5938 1.0000
2.750 0.7545 0.00758 0.00244 -0.0970 0.5613 1.0000
3.000 0.7752 0.00776 0.00255 -0.0955 0.5469 1.0000
3.250 0.7962 0.00794 0.00267 -0.0941 0.5331 1.0000
3.500 0.8173 0.00813 0.00281 -0.0928 0.5192 1.0000
3.750 0.8385 0.00831 0.00295 -0.0914 0.5049 1.0000
4.000 0.8595 0.00850 0.00310 -0.0900 0.4895 1.0000
4.250 0.8802 0.00870 0.00325 -0.0886 0.4726 1.0000
4.500 0.9011 0.00889 0.00341 -0.0872 0.4514 1.0000
4.750 0.9201 0.00914 0.00357 -0.0854 0.4239 1.0000
5.000 0.9369 0.00950 0.00377 -0.0832 0.3897 1.0000
5.250 0.9536 0.00991 0.00402 -0.0811 0.3633 1.0000
5.500 0.9721 0.01027 0.00430 -0.0794 0.3460 1.0000
5.750 0.9916 0.01059 0.00457 -0.0778 0.3325 1.0000
6.000 1.0114 0.01089 0.00484 -0.0763 0.3197 1.0000
6.250 1.0313 0.01119 0.00511 -0.0749 0.3076 1.0000
6.500 1.0511 0.01149 0.00539 -0.0734 0.2960 1.0000
6.750 1.0715 0.01176 0.00564 -0.0721 0.2830 1.0000
7.000 1.0916 0.01203 0.00589 -0.0707 0.2651 1.0000
7.250 1.1091 0.01242 0.00617 -0.0689 0.2368 1.0000
7.500 1.1195 0.01316 0.00663 -0.0659 0.1856 1.0000
7.750 1.1079 0.01501 0.00779 -0.0593 0.0775 1.0000
8.000 1.1085 0.01634 0.00880 -0.0547 0.0298 1.0000
8.250 1.1214 0.01699 0.00947 -0.0522 0.0241 1.0000
8.500 1.1320 0.01780 0.01032 -0.0494 0.0207 1.0000
8.750 1.1461 0.01840 0.01099 -0.0473 0.0198 1.0000
9.000 1.1584 0.01912 0.01178 -0.0449 0.0186 1.0000
9.250 1.1686 0.01996 0.01269 -0.0423 0.0176 1.0000
9.500 1.1766 0.02093 0.01374 -0.0396 0.0168 1.0000
9.750 1.1787 0.02227 0.01518 -0.0362 0.0160 1.0000
10.000 1.1802 0.02371 0.01672 -0.0329 0.0155 1.0000
10.250 1.1882 0.02480 0.01789 -0.0306 0.0151 1.0000
10.500 1.1978 0.02582 0.01898 -0.0287 0.0143 1.0000
10.750 1.2028 0.02721 0.02046 -0.0265 0.0141 1.0000
11.000 1.2068 0.02875 0.02208 -0.0243 0.0137 1.0000
11.250 1.2109 0.03036 0.02378 -0.0223 0.0133 1.0000
11.500 1.2143 0.03211 0.02561 -0.0205 0.0130 1.0000
11.750 1.2175 0.03395 0.02752 -0.0188 0.0127 1.0000
12.000 1.2199 0.03596 0.02959 -0.0172 0.0125 1.0000
12.250 1.2225 0.03802 0.03172 -0.0158 0.0122 1.0000
12.500 1.2250 0.04022 0.03398 -0.0142 0.0120 1.0000
12.750 1.2314 0.04276 0.03657 -0.0121 0.0116 1.0000
13.000 1.2383 0.04460 0.03853 -0.0110 0.0115 1.0000
13.250 1.2408 0.04655 0.04064 -0.0104 0.0112 1.0000
13.500 1.2467 0.04867 0.04288 -0.0094 0.0110 1.0000
13.750 1.2506 0.05089 0.04524 -0.0087 0.0108 1.0000
14.000 1.2537 0.05334 0.04783 -0.0080 0.0106 1.0000
14.250 1.2549 0.05595 0.05058 -0.0075 0.0103 1.0000
14.500 1.2558 0.05891 0.05371 -0.0068 0.0103 1.0000
14.750 1.2547 0.06201 0.05696 -0.0066 0.0102 1.0000
15.000 1.2515 0.06546 0.06057 -0.0065 0.0101 1.0000
15.250 1.2463 0.06924 0.06453 -0.0067 0.0100 1.0000
15.500 1.2400 0.07327 0.06872 -0.0073 0.0099 1.0000
15.750 1.2297 0.07809 0.07375 -0.0082 0.0099 1.0000
16.000 1.2197 0.08293 0.07876 -0.0096 0.0098 1.0000
16.250 1.2044 0.08893 0.08498 -0.0114 0.0100 1.0000
16.500 1.1885 0.09521 0.09146 -0.0138 0.0101 1.0000
16.750 1.1712 0.10198 0.09842 -0.0168 0.0102 1.0000
17.000 1.1533 0.10918 0.10581 -0.0203 0.0103 1.0000
17.250 1.1364 0.11649 0.11328 -0.0242 0.0105 1.0000
17.500 1.1151 0.12501 0.12197 -0.0289 0.0108 1.0000
17.750 1.0972 0.13322 0.13034 -0.0338 0.0109 1.0000
18.000 1.0770 0.14249 0.13976 -0.0396 0.0109 1.0000
18.250 1.0576 0.15194 0.14934 -0.0455 0.0110 1.0000
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