DEFIANT CANARD BL145 AIRFOIL (defcnd3-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL145 AIRFOIL (defcnd3-il) Reynolds number: 50,000 Max Cl/Cd: 25.64 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-defcnd3-il-50000.txt Download as CSV file: xf-defcnd3-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: DEFIANT CANARD BL145 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3883 0.09367 0.08711 -0.0049 1.0000 0.3456
-7.000 -0.3769 0.08818 0.08178 -0.0015 1.0000 0.3793
-6.750 -0.3527 0.08371 0.07732 -0.0005 1.0000 0.3907
-6.500 -0.3508 0.08101 0.07471 0.0011 1.0000 0.4057
-6.250 -0.3525 0.07853 0.07236 0.0032 1.0000 0.4215
-6.000 -0.3597 0.07638 0.07034 0.0057 1.0000 0.4376
-5.750 -0.4642 0.05390 0.04696 -0.0294 1.0000 0.1454
-5.500 -0.4569 0.04895 0.04152 -0.0291 1.0000 0.1282
-5.250 -0.4463 0.04496 0.03690 -0.0279 1.0000 0.1173
-5.000 -0.4330 0.04169 0.03331 -0.0265 1.0000 0.1125
-4.750 -0.4183 0.03889 0.02959 -0.0244 1.0000 0.1062
-4.500 -0.4006 0.03656 0.02697 -0.0228 1.0000 0.1049
-4.250 -0.3823 0.03435 0.02448 -0.0212 1.0000 0.1046
-4.000 -0.3636 0.03248 0.02230 -0.0196 1.0000 0.1062
-3.750 -0.3449 0.03063 0.02047 -0.0184 1.0000 0.1101
-3.500 -0.3252 0.02925 0.01896 -0.0169 1.0000 0.1143
-3.250 -0.3045 0.02805 0.01752 -0.0153 1.0000 0.1190
-3.000 -0.2840 0.02671 0.01625 -0.0139 1.0000 0.1269
-2.750 -0.2641 0.02567 0.01524 -0.0125 1.0000 0.1412
-2.500 -0.2437 0.02458 0.01423 -0.0112 1.0000 0.1705
-2.250 -0.0597 0.02104 0.01388 -0.0248 1.0000 1.0000
-2.000 -0.0997 0.02065 0.01361 -0.0179 1.0000 1.0000
-1.750 -0.1221 0.02054 0.01340 -0.0131 1.0000 1.0000
-1.500 -0.1254 0.02075 0.01337 -0.0105 1.0000 1.0000
-1.250 -0.1204 0.02115 0.01351 -0.0089 1.0000 1.0000
-1.000 -0.0969 0.02182 0.01388 -0.0105 0.9952 1.0000
-0.750 -0.0323 0.02286 0.01453 -0.0190 0.9757 1.0000
-0.500 0.0252 0.02360 0.01496 -0.0259 0.9554 1.0000
-0.250 0.0806 0.02417 0.01530 -0.0320 0.9355 1.0000
0.000 0.1319 0.02462 0.01555 -0.0370 0.9148 1.0000
0.250 0.1878 0.02486 0.01563 -0.0423 0.8929 1.0000
0.500 0.2626 0.02459 0.01523 -0.0500 0.8710 1.0000
0.750 0.3203 0.02428 0.01483 -0.0544 0.8475 1.0000
1.000 0.3696 0.02407 0.01454 -0.0572 0.8254 1.0000
1.250 0.4143 0.02395 0.01435 -0.0593 0.8046 1.0000
1.500 0.4555 0.02385 0.01419 -0.0605 0.7837 1.0000
1.750 0.4930 0.02382 0.01407 -0.0610 0.7627 1.0000
2.000 0.5243 0.02394 0.01412 -0.0604 0.7411 1.0000
2.250 0.5465 0.02436 0.01449 -0.0587 0.7177 1.0000
2.500 0.5720 0.02467 0.01474 -0.0574 0.6949 1.0000
2.750 0.5985 0.02498 0.01496 -0.0561 0.6731 1.0000
3.000 0.6253 0.02529 0.01518 -0.0548 0.6517 1.0000
3.250 0.6461 0.02589 0.01572 -0.0529 0.6294 1.0000
3.500 0.6665 0.02658 0.01637 -0.0512 0.6080 1.0000
3.750 0.6880 0.02728 0.01703 -0.0496 0.5881 1.0000
4.000 0.7095 0.02802 0.01776 -0.0481 0.5696 1.0000
4.250 0.7307 0.02885 0.01857 -0.0466 0.5528 1.0000
4.500 0.7531 0.02968 0.01937 -0.0454 0.5378 1.0000
4.750 0.7783 0.03036 0.02000 -0.0444 0.5240 1.0000
5.000 0.7934 0.03166 0.02143 -0.0427 0.5098 1.0000
5.250 0.8095 0.03302 0.02288 -0.0413 0.4971 1.0000
5.500 0.8341 0.03382 0.02366 -0.0403 0.4858 1.0000
5.750 0.8511 0.03507 0.02501 -0.0388 0.4734 1.0000
6.000 0.8636 0.03668 0.02678 -0.0371 0.4611 1.0000
6.250 0.8857 0.03739 0.02751 -0.0357 0.4476 1.0000
6.500 0.9112 0.03763 0.02772 -0.0343 0.4324 1.0000
6.750 0.9363 0.03780 0.02785 -0.0329 0.4161 1.0000
7.000 0.9615 0.03799 0.02802 -0.0315 0.3999 1.0000
7.250 0.9781 0.03883 0.02897 -0.0296 0.3838 1.0000
7.500 0.9975 0.03946 0.02964 -0.0278 0.3670 1.0000
7.750 1.0200 0.03986 0.03005 -0.0262 0.3491 1.0000
8.000 1.0386 0.04057 0.03077 -0.0243 0.3304 1.0000
8.250 1.0511 0.04182 0.03213 -0.0220 0.3118 1.0000
8.500 1.0636 0.04310 0.03351 -0.0197 0.2929 1.0000
8.750 1.0771 0.04454 0.03500 -0.0176 0.2756 1.0000
9.000 1.0904 0.04608 0.03657 -0.0156 0.2599 1.0000
9.250 1.1065 0.04766 0.03815 -0.0140 0.2464 1.0000
9.500 1.1324 0.04881 0.03914 -0.0132 0.2329 1.0000
9.750 1.1051 0.05342 0.04433 -0.0091 0.2276 1.0000
10.000 1.1416 0.05418 0.04485 -0.0091 0.2160 1.0000
10.250 1.1065 0.05938 0.05053 -0.0052 0.2138 1.0000
10.500 1.0630 0.06530 0.05671 -0.0021 0.2133 1.0000
10.750 1.0090 0.07288 0.06441 -0.0009 0.2144 1.0000
11.000 0.9488 0.08416 0.07569 -0.0049 0.2161 1.0000
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Polar data table (+)
Polar graphs
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