Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn) Reynolds number: 1,000,000 Max Cl/Cd: 58.34 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cp-100-050-gn-1000000-n5.txt Download as CSV file: xf-cp-100-050-gn-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=10% T=5% R=1.3
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.1618 0.14752 0.14531 -0.1076 0.9743 0.0159
-13.750 -0.1508 0.14453 0.14232 -0.1098 0.9737 0.0165
-13.500 -0.1470 0.13937 0.13714 -0.1124 0.9730 0.0173
-13.250 -0.1329 0.13710 0.13487 -0.1147 0.9724 0.0175
-13.000 -0.1206 0.13420 0.13196 -0.1171 0.9719 0.0175
-12.750 -0.1121 0.13249 0.13025 -0.1176 0.9689 0.0177
-12.500 -0.1025 0.13005 0.12781 -0.1190 0.9667 0.0178
-12.250 -0.0909 0.12771 0.12547 -0.1207 0.9649 0.0182
-12.000 -0.0791 0.12499 0.12274 -0.1228 0.9635 0.0186
-10.000 0.0214 0.10289 0.10056 -0.1411 0.9484 0.0213
-9.500 0.0472 0.09498 0.09259 -0.1488 0.9445 0.0226
-9.250 0.0598 0.09329 0.09090 -0.1498 0.9406 0.0227
-9.000 0.0750 0.09121 0.08882 -0.1519 0.9371 0.0229
-8.750 0.0932 0.08891 0.08650 -0.1549 0.9342 0.0230
-8.500 0.1148 0.08669 0.08426 -0.1585 0.9319 0.0234
-8.250 0.1364 0.08408 0.08162 -0.1626 0.9295 0.0238
-8.000 0.1477 0.08179 0.07933 -0.1641 0.9248 0.0240
-7.500 0.1741 0.07535 0.07281 -0.1705 0.9152 0.0256
-7.250 0.1892 0.07330 0.07074 -0.1725 0.9110 0.0256
-7.000 0.2011 0.07160 0.06904 -0.1734 0.9056 0.0257
-6.750 0.2186 0.07032 0.06774 -0.1748 0.9009 0.0261
-6.500 0.2341 0.06834 0.06573 -0.1768 0.8962 0.0263
-6.250 0.2434 0.06685 0.06425 -0.1768 0.8907 0.0267
-6.000 0.2527 0.06493 0.06231 -0.1775 0.8845 0.0270
-5.750 0.2606 0.06292 0.06027 -0.1781 0.8786 0.0276
-5.500 0.2539 0.06011 0.05745 -0.1775 0.8706 0.0285
-5.250 0.2677 0.05883 0.05615 -0.1782 0.8655 0.0287
-5.000 0.2813 0.05755 0.05486 -0.1788 0.8607 0.0288
-4.750 0.2931 0.05605 0.05336 -0.1793 0.8554 0.0290
-4.500 0.3076 0.05475 0.05205 -0.1800 0.8503 0.0294
-4.250 0.3226 0.05315 0.05042 -0.1812 0.8454 0.0298
-4.000 0.3357 0.05133 0.04860 -0.1821 0.8400 0.0301
-3.500 0.3637 0.04558 0.04273 -0.1872 0.8263 0.0317
-3.250 0.3809 0.04443 0.04156 -0.1875 0.8172 0.0319
-3.000 0.3996 0.04338 0.04046 -0.1880 0.8099 0.0321
-2.750 0.4183 0.04210 0.03917 -0.1886 0.8011 0.0323
-2.500 0.4380 0.04065 0.03767 -0.1895 0.7939 0.0327
-2.250 0.4577 0.03902 0.03598 -0.1906 0.7832 0.0330
-1.750 0.5058 0.03340 0.03017 -0.1962 0.7651 0.0350
-1.500 0.5261 0.03248 0.02919 -0.1960 0.7544 0.0352
-1.250 0.5443 0.03168 0.02831 -0.1952 0.7392 0.0354
-1.000 0.5637 0.03075 0.02731 -0.1947 0.7242 0.0357
-0.750 0.5786 0.02971 0.02612 -0.1933 0.6984 0.0359
-0.500 0.5938 0.02866 0.02494 -0.1918 0.6738 0.0363
-0.250 0.6030 0.02766 0.02374 -0.1888 0.6411 0.0367
0.250 0.6215 0.02405 0.01954 -0.1834 0.5548 0.0386
0.500 0.5971 0.02505 0.01981 -0.1731 0.3966 0.0387
0.750 0.5741 0.02643 0.02032 -0.1636 0.1658 0.0387
1.000 0.5829 0.02645 0.01996 -0.1604 0.0424 0.0388
1.250 0.6056 0.02586 0.01931 -0.1598 0.0371 0.0391
1.500 0.6297 0.02500 0.01836 -0.1596 0.0345 0.0395
1.750 0.6557 0.02380 0.01705 -0.1596 0.0332 0.0400
2.000 0.6956 0.01905 0.01177 -0.1626 0.0328 0.0425
2.250 0.7181 0.01872 0.01136 -0.1615 0.0320 0.0428
2.500 0.7411 0.01806 0.01056 -0.1606 0.0312 0.0432
2.750 0.7659 0.01592 0.00786 -0.1599 0.0307 0.0455
3.000 0.7871 0.01574 0.00754 -0.1584 0.0302 0.0458
3.250 0.8080 0.01557 0.00727 -0.1570 0.0297 0.0461
3.500 0.8282 0.01563 0.00730 -0.1553 0.0293 0.0464
3.750 0.8477 0.01575 0.00739 -0.1535 0.0288 0.0466
4.000 0.8679 0.01589 0.00752 -0.1519 0.0286 0.0469
4.250 0.8879 0.01601 0.00762 -0.1502 0.0284 0.0472
4.500 0.9078 0.01614 0.00772 -0.1485 0.0283 0.0474
4.750 0.9270 0.01632 0.00789 -0.1467 0.0281 0.0477
5.000 0.9460 0.01650 0.00805 -0.1448 0.0279 0.0481
5.250 0.9647 0.01674 0.00828 -0.1429 0.0278 0.0487
5.500 0.9834 0.01697 0.00850 -0.1411 0.0276 0.0489
5.750 1.0020 0.01721 0.00872 -0.1392 0.0274 0.0492
6.000 1.0198 0.01748 0.00900 -0.1372 0.0273 0.0494
6.250 1.0373 0.01780 0.00932 -0.1352 0.0271 0.0497
6.500 1.0549 0.01813 0.00966 -0.1332 0.0270 0.0498
6.750 1.0726 0.01847 0.01000 -0.1313 0.0268 0.0500
7.000 1.0891 0.01887 0.01041 -0.1291 0.0266 0.0501
7.250 1.1055 0.01924 0.01080 -0.1270 0.0265 0.0504
7.500 1.1224 0.01963 0.01120 -0.1250 0.0262 0.0507
7.750 1.1393 0.02005 0.01164 -0.1231 0.0260 0.0511
8.000 1.1553 0.02054 0.01215 -0.1210 0.0258 0.0517
8.250 1.1704 0.02107 0.01271 -0.1188 0.0256 0.0520
8.500 1.1857 0.02162 0.01327 -0.1166 0.0255 0.0524
8.750 1.2002 0.02224 0.01391 -0.1144 0.0253 0.0527
9.000 1.2134 0.02294 0.01465 -0.1121 0.0251 0.0534
9.250 1.2257 0.02374 0.01547 -0.1096 0.0249 0.0537
9.500 1.2367 0.02465 0.01643 -0.1071 0.0247 0.0539
9.750 1.2511 0.02535 0.01715 -0.1050 0.0247 0.0542
10.000 1.2662 0.02602 0.01786 -0.1031 0.0246 0.0548
10.250 1.2816 0.02668 0.01854 -0.1012 0.0245 0.0553
10.500 1.2952 0.02748 0.01939 -0.0992 0.0244 0.0563
10.750 1.3101 0.02821 0.02015 -0.0973 0.0243 0.0573
11.000 1.3240 0.02904 0.02102 -0.0954 0.0242 0.0585
11.250 1.3385 0.02984 0.02186 -0.0936 0.0241 0.0605
11.500 1.3526 0.03068 0.02274 -0.0917 0.0239 0.0638
11.750 1.3666 0.03155 0.02366 -0.0899 0.0238 0.0697
12.000 1.3803 0.03216 0.02480 -0.0881 0.0237 0.4667
12.500 1.4480 0.03402 0.02753 -0.0932 0.0233 1.0000
12.750 1.4615 0.03496 0.02850 -0.0915 0.0231 1.0000
13.000 1.4750 0.03591 0.02947 -0.0897 0.0229 1.0000
13.250 1.4879 0.03691 0.03050 -0.0879 0.0228 1.0000
13.500 1.5012 0.03789 0.03151 -0.0861 0.0226 1.0000
13.750 1.5137 0.03892 0.03257 -0.0844 0.0225 1.0000
14.000 1.5259 0.04001 0.03369 -0.0826 0.0224 1.0000
14.250 1.5384 0.04107 0.03479 -0.0809 0.0223 1.0000
14.500 1.5506 0.04217 0.03592 -0.0792 0.0222 1.0000
14.750 1.5622 0.04334 0.03713 -0.0776 0.0221 1.0000
15.000 1.5736 0.04453 0.03835 -0.0759 0.0220 1.0000
15.250 1.5850 0.04571 0.03957 -0.0743 0.0219 1.0000
15.500 1.5955 0.04698 0.04088 -0.0727 0.0217 1.0000
15.750 1.6058 0.04832 0.04226 -0.0711 0.0217 1.0000
16.000 1.6160 0.04966 0.04364 -0.0696 0.0216 1.0000
16.250 1.6258 0.05106 0.04509 -0.0680 0.0215 1.0000
16.500 1.6349 0.05256 0.04663 -0.0665 0.0214 1.0000
16.750 1.6437 0.05410 0.04822 -0.0650 0.0213 1.0000
17.000 1.6522 0.05571 0.04989 -0.0635 0.0212 1.0000
17.250 1.6594 0.05759 0.05186 -0.0619 0.0209 1.0000
17.500 1.6664 0.05938 0.05374 -0.0605 0.0209 1.0000
17.750 1.6732 0.06121 0.05565 -0.0592 0.0209 1.0000
18.000 1.6790 0.06317 0.05770 -0.0580 0.0208 1.0000
18.250 1.6843 0.06519 0.05981 -0.0568 0.0207 1.0000
18.500 1.6890 0.06731 0.06203 -0.0557 0.0206 1.0000
18.750 1.6927 0.06958 0.06440 -0.0547 0.0205 1.0000
19.000 1.6959 0.07198 0.06691 -0.0537 0.0204 1.0000
19.250 1.6977 0.07460 0.06964 -0.0529 0.0203 1.0000
19.500 1.6986 0.07738 0.07254 -0.0521 0.0202 1.0000
19.750 1.6984 0.08033 0.07561 -0.0515 0.0201 1.0000
20.000 1.6961 0.08363 0.07905 -0.0511 0.0200 1.0000
20.250 1.6932 0.08707 0.08262 -0.0508 0.0199 1.0000
20.500 1.6892 0.09070 0.08639 -0.0508 0.0197 1.0000
20.750 1.6823 0.09487 0.09072 -0.0510 0.0196 1.0000
21.000 1.6753 0.09912 0.09511 -0.0515 0.0195 1.0000
21.250 1.6665 0.10371 0.09986 -0.0524 0.0194 1.0000
21.500 1.6556 0.10873 0.10504 -0.0536 0.0193 1.0000
21.750 1.6442 0.11398 0.11044 -0.0553 0.0191 1.0000
22.000 1.6285 0.12011 0.11674 -0.0576 0.0191 1.0000
22.250 1.6119 0.12657 0.12338 -0.0605 0.0190 1.0000
|
Polar data table (+)
Polar graphs
<< Back to Cambered plate C=10% T=5% R=1.3 (cp-100-050-gn)