ARA-D 6% AIRFOIL (arad6-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: ARA-D 6% AIRFOIL (arad6-il) Reynolds number: 500,000 Max Cl/Cd: 122.48 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-arad6-il-500000.txt Download as CSV file: xf-arad6-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 6% 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 -0.2864 0.10688 0.10475 -0.0263 1.0000 0.0162
-9.250 -0.2926 0.10483 0.10274 -0.0255 1.0000 0.0163
-9.000 -0.2994 0.10283 0.10076 -0.0244 1.0000 0.0163
-8.750 -0.2922 0.09871 0.09665 -0.0275 0.9987 0.0164
-8.500 -0.2838 0.09448 0.09242 -0.0304 0.9972 0.0164
-8.250 -0.2761 0.08879 0.08674 -0.0321 0.9960 0.0168
-8.000 -0.2619 0.08494 0.08288 -0.0333 0.9950 0.0171
-7.750 -0.2503 0.08128 0.07922 -0.0354 0.9933 0.0176
-7.500 -0.2399 0.07761 0.07555 -0.0377 0.9907 0.0182
-7.250 -0.3473 0.08947 0.08734 -0.0304 0.9948 0.0169
-7.000 -0.3287 0.08615 0.08401 -0.0331 0.9928 0.0174
-6.750 -0.3071 0.08254 0.08039 -0.0379 0.9898 0.0180
-6.500 -0.2814 0.07847 0.07630 -0.0443 0.9872 0.0189
-6.250 -0.2500 0.07375 0.07155 -0.0527 0.9851 0.0204
-6.000 -0.1945 0.06728 0.06500 -0.0703 0.9834 0.0218
-5.750 -0.1719 0.06098 0.05867 -0.0767 0.9788 0.0224
-5.500 -0.1452 0.05796 0.05563 -0.0802 0.9765 0.0230
-5.250 -0.1119 0.05461 0.05223 -0.0856 0.9747 0.0239
-5.000 -0.0714 0.05049 0.04804 -0.0932 0.9735 0.0255
-4.750 -0.0065 0.04424 0.04158 -0.1068 0.9727 0.0287
-4.500 0.0354 0.03711 0.03428 -0.1158 0.9720 0.0302
-4.250 0.0710 0.03497 0.03208 -0.1195 0.9710 0.0316
-4.000 0.1092 0.03174 0.02868 -0.1238 0.9680 0.0342
-3.750 0.1825 0.01487 0.00987 -0.1368 0.9699 0.0225
-3.500 0.2138 0.01344 0.00814 -0.1375 0.9653 0.0224
-3.250 0.2476 0.01205 0.00652 -0.1388 0.9622 0.0230
-3.000 0.2812 0.01129 0.00566 -0.1399 0.9594 0.0242
-2.750 0.3142 0.01074 0.00505 -0.1408 0.9566 0.0256
-2.500 0.3417 0.01036 0.00461 -0.1406 0.9500 0.0273
-2.250 0.3718 0.00992 0.00411 -0.1408 0.9451 0.0298
-2.000 0.4008 0.00953 0.00371 -0.1408 0.9398 0.0348
-1.750 0.4291 0.00915 0.00335 -0.1406 0.9331 0.0531
-1.500 0.4572 0.00898 0.00322 -0.1404 0.9277 0.0723
-1.250 0.4843 0.00888 0.00314 -0.1401 0.9197 0.0880
-1.000 0.5120 0.00875 0.00304 -0.1398 0.9137 0.1065
-0.750 0.5394 0.00865 0.00300 -0.1396 0.9052 0.1275
-0.500 0.5664 0.00855 0.00290 -0.1391 0.8960 0.1475
-0.250 0.5929 0.00840 0.00278 -0.1385 0.8827 0.1671
0.000 0.6197 0.00830 0.00267 -0.1379 0.8685 0.1886
0.250 0.6471 0.00820 0.00261 -0.1376 0.8555 0.2170
0.500 0.6746 0.00807 0.00257 -0.1374 0.8411 0.2673
0.750 0.6952 0.00646 0.00255 -0.1359 0.8276 1.0000
1.000 0.7229 0.00653 0.00251 -0.1356 0.8137 1.0000
1.250 0.7506 0.00661 0.00250 -0.1354 0.7994 1.0000
1.500 0.7781 0.00671 0.00251 -0.1352 0.7839 1.0000
1.750 0.8056 0.00682 0.00254 -0.1349 0.7671 1.0000
2.000 0.8330 0.00694 0.00258 -0.1347 0.7487 1.0000
2.250 0.8601 0.00709 0.00262 -0.1344 0.7283 1.0000
2.500 0.8871 0.00726 0.00269 -0.1341 0.7056 1.0000
2.750 0.9137 0.00746 0.00279 -0.1337 0.6800 1.0000
3.000 0.9401 0.00769 0.00289 -0.1333 0.6509 1.0000
3.250 0.9660 0.00797 0.00302 -0.1328 0.6154 1.0000
3.500 0.9916 0.00830 0.00318 -0.1323 0.5760 1.0000
3.750 1.0159 0.00877 0.00341 -0.1317 0.5218 1.0000
4.000 1.0391 0.00941 0.00370 -0.1309 0.4505 1.0000
4.250 1.0612 0.01024 0.00409 -0.1300 0.3637 1.0000
4.500 1.0836 0.01104 0.00451 -0.1292 0.2931 1.0000
4.750 1.1076 0.01162 0.00490 -0.1287 0.2533 1.0000
5.000 1.1322 0.01212 0.00525 -0.1282 0.2250 1.0000
5.250 1.1569 0.01257 0.00559 -0.1278 0.2045 1.0000
5.500 1.1818 0.01296 0.00592 -0.1273 0.1875 1.0000
5.750 1.2067 0.01336 0.00628 -0.1269 0.1722 1.0000
6.000 1.2314 0.01375 0.00663 -0.1264 0.1584 1.0000
6.250 1.2558 0.01416 0.00700 -0.1259 0.1459 1.0000
6.500 1.2801 0.01457 0.00737 -0.1253 0.1342 1.0000
6.750 1.3045 0.01496 0.00776 -0.1248 0.1229 1.0000
7.000 1.3284 0.01538 0.00817 -0.1242 0.1117 1.0000
7.250 1.3518 0.01584 0.00862 -0.1235 0.1015 1.0000
7.500 1.3746 0.01636 0.00911 -0.1227 0.0915 1.0000
8.000 1.4195 0.01739 0.01011 -0.1211 0.0717 1.0000
8.250 1.4415 0.01791 0.01064 -0.1202 0.0636 1.0000
8.500 1.4622 0.01857 0.01127 -0.1191 0.0561 1.0000
8.750 1.4839 0.01907 0.01182 -0.1181 0.0508 1.0000
9.000 1.5034 0.01980 0.01256 -0.1168 0.0452 1.0000
9.250 1.5245 0.02029 0.01312 -0.1158 0.0409 1.0000
9.500 1.5426 0.02108 0.01390 -0.1143 0.0357 1.0000
9.750 1.5628 0.02158 0.01447 -0.1131 0.0313 1.0000
10.000 1.5800 0.02238 0.01528 -0.1115 0.0257 1.0000
10.250 1.5943 0.02341 0.01631 -0.1093 0.0193 1.0000
10.500 1.6048 0.02473 0.01767 -0.1066 0.0150 1.0000
10.750 1.6183 0.02566 0.01871 -0.1043 0.0133 1.0000
11.000 1.6283 0.02676 0.01989 -0.1014 0.0121 1.0000
11.250 1.6291 0.02840 0.02164 -0.0971 0.0111 1.0000
11.500 1.6346 0.02975 0.02313 -0.0938 0.0106 1.0000
11.750 1.6414 0.03105 0.02457 -0.0908 0.0101 1.0000
12.000 1.6474 0.03245 0.02609 -0.0880 0.0095 1.0000
12.250 1.6525 0.03397 0.02773 -0.0852 0.0091 1.0000
12.500 1.6557 0.03569 0.02958 -0.0825 0.0087 1.0000
12.750 1.6551 0.03780 0.03183 -0.0796 0.0084 1.0000
13.000 1.6498 0.04046 0.03463 -0.0765 0.0081 1.0000
13.250 1.6408 0.04363 0.03797 -0.0736 0.0079 1.0000
13.500 1.6284 0.04738 0.04192 -0.0709 0.0078 1.0000
13.750 1.6248 0.05033 0.04503 -0.0692 0.0077 1.0000
14.000 1.6204 0.05354 0.04841 -0.0679 0.0076 1.0000
14.250 1.6138 0.05717 0.05222 -0.0669 0.0075 1.0000
14.500 1.6056 0.06117 0.05639 -0.0663 0.0075 1.0000
14.750 1.5957 0.06561 0.06102 -0.0662 0.0074 1.0000
15.000 1.5846 0.07052 0.06611 -0.0666 0.0073 1.0000
15.250 1.5720 0.07591 0.07168 -0.0675 0.0073 1.0000
15.500 1.5585 0.08178 0.07773 -0.0691 0.0072 1.0000
15.750 1.5435 0.08821 0.08434 -0.0712 0.0072 1.0000
16.000 1.5274 0.09518 0.09149 -0.0740 0.0072 1.0000
16.250 1.5103 0.10263 0.09911 -0.0772 0.0072 1.0000
16.500 1.4928 0.11052 0.10718 -0.0811 0.0072 1.0000
16.750 1.4746 0.11885 0.11567 -0.0854 0.0072 1.0000
17.000 1.4563 0.12746 0.12445 -0.0900 0.0072 1.0000
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