Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Cambered plate C=8% T=5% R=1.6 (cp-080-050-gn) Reynolds number: 500,000 Max Cl/Cd: 44.82 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cp-080-050-gn-500000-n5.txt Download as CSV file: xf-cp-080-050-gn-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Cambered plate C=8% T=5% R=1.6
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1297 0.10190 0.09886 -0.0946 0.9670 0.0340
-8.000 -0.1180 0.09970 0.09667 -0.0958 0.9642 0.0342
-7.750 -0.1022 0.09785 0.09483 -0.0974 0.9622 0.0346
-7.500 -0.0878 0.09532 0.09231 -0.0996 0.9605 0.0349
-7.250 -0.0727 0.09265 0.08964 -0.1021 0.9590 0.0353
-7.000 -0.0574 0.08976 0.08674 -0.1050 0.9576 0.0358
-6.750 -0.0412 0.08667 0.08365 -0.1083 0.9564 0.0359
-6.500 -0.0348 0.08424 0.08122 -0.1090 0.9509 0.0364
-6.250 -0.0272 0.07975 0.07671 -0.1133 0.9469 0.0374
-6.000 -0.0069 0.07770 0.07466 -0.1159 0.9449 0.0376
-5.750 0.0166 0.07565 0.07262 -0.1192 0.9434 0.0380
-5.500 0.0401 0.07290 0.06987 -0.1237 0.9418 0.0384
-5.250 0.0484 0.07090 0.06787 -0.1243 0.9349 0.0387
-5.000 0.0646 0.06829 0.06525 -0.1274 0.9303 0.0391
-4.750 0.0839 0.06529 0.06223 -0.1318 0.9264 0.0396
-4.500 0.0808 0.06104 0.05793 -0.1354 0.9158 0.0409
-4.250 0.1019 0.05920 0.05609 -0.1378 0.9118 0.0411
-4.000 0.1202 0.05752 0.05440 -0.1393 0.9050 0.0414
-3.750 0.1348 0.05585 0.05273 -0.1403 0.8981 0.0417
-3.500 0.1564 0.05362 0.05044 -0.1432 0.8901 0.0420
-3.250 0.1706 0.05142 0.04818 -0.1445 0.8761 0.0423
-3.000 0.1857 0.04931 0.04603 -0.1457 0.8667 0.0428
-2.750 0.2049 0.04688 0.04351 -0.1479 0.8563 0.0434
-2.500 0.2197 0.04248 0.03897 -0.1516 0.8468 0.0448
-2.250 0.2412 0.04116 0.03759 -0.1522 0.8381 0.0450
-2.000 0.2603 0.03991 0.03632 -0.1521 0.8288 0.0452
-1.750 0.2810 0.03842 0.03475 -0.1525 0.8153 0.0456
-1.500 0.3015 0.03669 0.03292 -0.1529 0.8016 0.0459
-1.000 0.3467 0.02927 0.02504 -0.1564 0.7793 0.0486
-0.750 0.3652 0.02854 0.02419 -0.1550 0.7522 0.0487
-0.500 0.3812 0.02793 0.02338 -0.1530 0.7164 0.0489
-0.250 0.3921 0.02745 0.02262 -0.1498 0.6641 0.0492
0.250 0.3631 0.02917 0.02254 -0.1335 0.2572 0.0494
0.500 0.3654 0.02947 0.02219 -0.1290 0.0632 0.0497
0.750 0.3856 0.02846 0.02108 -0.1278 0.0561 0.0503
1.000 0.4064 0.02686 0.01934 -0.1267 0.0537 0.0511
1.250 0.4281 0.02174 0.01362 -0.1258 0.0527 0.0531
1.500 0.4480 0.02156 0.01341 -0.1242 0.0507 0.0533
1.750 0.4678 0.02137 0.01318 -0.1224 0.0491 0.0536
2.000 0.4883 0.02089 0.01263 -0.1208 0.0481 0.0541
2.250 0.5090 0.02007 0.01166 -0.1192 0.0471 0.0547
2.500 0.5300 0.01906 0.01042 -0.1176 0.0463 0.0554
2.750 0.5512 0.01804 0.00913 -0.1160 0.0457 0.0564
3.000 0.5723 0.01743 0.00825 -0.1143 0.0451 0.0574
3.250 0.5924 0.01735 0.00813 -0.1125 0.0445 0.0577
3.500 0.6119 0.01741 0.00816 -0.1106 0.0439 0.0580
3.750 0.6324 0.01738 0.00810 -0.1089 0.0437 0.0583
4.000 0.6532 0.01738 0.00806 -0.1072 0.0433 0.0586
4.250 0.6735 0.01744 0.00809 -0.1054 0.0430 0.0590
4.500 0.6935 0.01749 0.00811 -0.1036 0.0427 0.0595
4.750 0.7133 0.01757 0.00815 -0.1017 0.0423 0.0598
5.000 0.7327 0.01769 0.00824 -0.0998 0.0420 0.0603
5.250 0.7519 0.01784 0.00835 -0.0978 0.0416 0.0609
5.500 0.7707 0.01803 0.00851 -0.0958 0.0412 0.0615
5.750 0.7897 0.01823 0.00868 -0.0938 0.0409 0.0619
6.000 0.8085 0.01843 0.00886 -0.0918 0.0404 0.0622
6.250 0.8267 0.01864 0.00906 -0.0898 0.0401 0.0624
6.500 0.8443 0.01892 0.00936 -0.0877 0.0398 0.0629
6.750 0.8618 0.01923 0.00969 -0.0856 0.0395 0.0632
7.000 0.8787 0.01962 0.01008 -0.0834 0.0393 0.0635
7.250 0.8952 0.02008 0.01054 -0.0812 0.0390 0.0639
7.500 0.9118 0.02057 0.01104 -0.0790 0.0388 0.0643
7.750 0.9301 0.02094 0.01144 -0.0771 0.0386 0.0650
8.000 0.9483 0.02137 0.01190 -0.0752 0.0385 0.0657
8.250 0.9669 0.02178 0.01233 -0.0734 0.0383 0.0662
8.500 0.9855 0.02222 0.01281 -0.0716 0.0381 0.0667
8.750 1.0043 0.02269 0.01330 -0.0698 0.0379 0.0672
9.000 1.0233 0.02315 0.01380 -0.0681 0.0376 0.0677
9.250 1.0424 0.02361 0.01430 -0.0664 0.0373 0.0684
9.500 1.0617 0.02410 0.01483 -0.0648 0.0369 0.0691
9.750 1.0812 0.02461 0.01538 -0.0633 0.0366 0.0701
10.000 1.1011 0.02516 0.01596 -0.0618 0.0364 0.0712
10.250 1.1210 0.02572 0.01655 -0.0603 0.0361 0.0725
10.500 1.1412 0.02631 0.01717 -0.0589 0.0360 0.0736
10.750 1.1606 0.02687 0.01778 -0.0575 0.0357 0.0760
11.000 1.1804 0.02749 0.01842 -0.0560 0.0355 0.0797
11.250 1.1999 0.02809 0.01907 -0.0546 0.0353 0.0864
11.500 1.2192 0.02861 0.01986 -0.0532 0.0351 0.2427
12.000 1.2922 0.02952 0.02194 -0.0577 0.0346 1.0000
12.250 1.3144 0.03043 0.02283 -0.0567 0.0344 1.0000
12.500 1.3369 0.03144 0.02387 -0.0558 0.0342 1.0000
12.750 1.3540 0.03232 0.02484 -0.0541 0.0340 1.0000
13.000 1.3697 0.03323 0.02585 -0.0523 0.0338 1.0000
13.250 1.3846 0.03421 0.02693 -0.0504 0.0335 1.0000
13.500 1.4001 0.03529 0.02812 -0.0487 0.0332 1.0000
13.750 1.4157 0.03648 0.02940 -0.0470 0.0330 1.0000
14.000 1.4298 0.03773 0.03076 -0.0452 0.0327 1.0000
14.250 1.4423 0.03904 0.03219 -0.0432 0.0325 1.0000
14.500 1.4530 0.04039 0.03365 -0.0412 0.0322 1.0000
14.750 1.4628 0.04182 0.03519 -0.0391 0.0320 1.0000
15.000 1.4709 0.04326 0.03673 -0.0369 0.0318 1.0000
15.250 1.4777 0.04477 0.03836 -0.0347 0.0316 1.0000
15.500 1.4835 0.04630 0.03998 -0.0324 0.0314 1.0000
15.750 1.4881 0.04791 0.04169 -0.0302 0.0313 1.0000
16.000 1.4911 0.04971 0.04361 -0.0280 0.0312 1.0000
16.250 1.4931 0.05158 0.04559 -0.0259 0.0311 1.0000
16.500 1.4935 0.05358 0.04770 -0.0239 0.0309 1.0000
16.750 1.4932 0.05566 0.04989 -0.0219 0.0308 1.0000
17.000 1.4927 0.05773 0.05207 -0.0202 0.0307 1.0000
17.250 1.4905 0.06007 0.05452 -0.0185 0.0306 1.0000
17.500 1.4889 0.06230 0.05683 -0.0171 0.0305 1.0000
17.750 1.4838 0.06513 0.05978 -0.0158 0.0305 1.0000
18.000 1.4813 0.06764 0.06237 -0.0148 0.0304 1.0000
18.250 1.4744 0.07090 0.06575 -0.0140 0.0303 1.0000
18.500 1.4672 0.07427 0.06924 -0.0136 0.0302 1.0000
18.750 1.4577 0.07812 0.07321 -0.0134 0.0301 1.0000
19.000 1.4443 0.08270 0.07794 -0.0138 0.0300 1.0000
19.250 1.4082 0.09087 0.08644 -0.0161 0.0299 1.0000
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Polar data table (+)
Polar graphs
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