JN-153 AIRFOIL (jn153-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: JN-153 AIRFOIL (jn153-il) Reynolds number: 1,000,000 Max Cl/Cd: 165.93 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-jn153-il-1000000-n5.txt Download as CSV file: xf-jn153-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: JN-153 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.000 0.1612 0.09653 0.09210 -0.0980 0.4615 0.0102
-9.750 0.1697 0.09408 0.08966 -0.0990 0.4615 0.0102
-9.500 0.1742 0.09078 0.08637 -0.1004 0.4613 0.0103
-9.250 0.1814 0.08810 0.08370 -0.1014 0.4611 0.0103
-9.000 0.1888 0.08549 0.08110 -0.1024 0.4611 0.0103
-8.750 0.1981 0.08352 0.07915 -0.1029 0.4609 0.0105
-8.500 0.2063 0.08128 0.07692 -0.1037 0.4607 0.0106
-8.250 0.2157 0.07931 0.07496 -0.1045 0.4606 0.0107
-8.000 0.2202 0.07639 0.07207 -0.1056 0.4605 0.0107
-7.750 0.2228 0.07315 0.06885 -0.1069 0.4603 0.0106
-7.500 0.2345 0.07185 0.06757 -0.1072 0.4602 0.0108
-7.250 0.2427 0.06989 0.06562 -0.1079 0.4600 0.0110
-7.000 0.2710 0.05491 0.05091 -0.1008 0.4593 0.0118
-6.500 0.1294 0.02283 0.01774 -0.1448 0.4600 0.0078
-6.250 0.1525 0.01891 0.01321 -0.1471 0.4597 0.0079
-6.000 0.1796 0.01726 0.01125 -0.1480 0.4593 0.0080
-5.750 0.2078 0.01644 0.01026 -0.1485 0.4589 0.0081
-5.500 0.2365 0.01586 0.00956 -0.1489 0.4587 0.0082
-5.250 0.2653 0.01542 0.00904 -0.1492 0.4584 0.0084
-5.000 0.2943 0.01506 0.00859 -0.1495 0.4581 0.0085
-4.750 0.3235 0.01469 0.00815 -0.1498 0.4580 0.0086
-4.500 0.3528 0.01436 0.00776 -0.1500 0.4579 0.0088
-4.250 0.3821 0.01405 0.00738 -0.1503 0.4579 0.0090
-4.000 0.4116 0.01375 0.00702 -0.1506 0.4578 0.0092
-3.750 0.4411 0.01349 0.00671 -0.1508 0.4577 0.0095
-3.500 0.4707 0.01325 0.00643 -0.1511 0.4576 0.0097
-3.250 0.5003 0.01305 0.00618 -0.1514 0.4574 0.0099
-3.000 0.5300 0.01285 0.00595 -0.1516 0.4572 0.0101
-2.750 0.5596 0.01267 0.00574 -0.1519 0.4569 0.0102
-2.500 0.5893 0.01250 0.00555 -0.1522 0.4567 0.0103
-2.250 0.6192 0.01228 0.00531 -0.1525 0.4564 0.0106
-2.000 0.6490 0.01215 0.00516 -0.1528 0.4561 0.0109
-1.750 0.6787 0.01205 0.00505 -0.1531 0.4559 0.0111
-1.500 0.7084 0.01196 0.00496 -0.1534 0.4555 0.0114
-1.250 0.7381 0.01189 0.00488 -0.1536 0.4552 0.0119
-1.000 0.7677 0.01184 0.00483 -0.1539 0.4548 0.0125
-0.750 0.7973 0.01180 0.00479 -0.1542 0.4545 0.0130
-0.500 0.8270 0.01172 0.00471 -0.1545 0.4540 0.0139
-0.250 0.8565 0.01166 0.00465 -0.1547 0.4533 0.0151
0.000 0.8861 0.01160 0.00459 -0.1550 0.4526 0.0174
0.250 0.9157 0.01154 0.00455 -0.1553 0.4520 0.0224
0.500 0.9452 0.01149 0.00453 -0.1556 0.4513 0.0334
0.750 0.9749 0.01141 0.00452 -0.1559 0.4507 0.0579
1.000 1.0047 0.01128 0.00453 -0.1564 0.4501 0.1122
1.250 1.0357 0.01093 0.00458 -0.1574 0.4495 0.2828
1.500 1.0656 0.01079 0.00466 -0.1580 0.4490 0.3792
1.750 1.0953 0.01072 0.00474 -0.1584 0.4485 0.4467
2.000 1.1249 0.01066 0.00482 -0.1589 0.4481 0.5133
2.250 1.1543 0.01063 0.00490 -0.1593 0.4476 0.5676
2.500 1.1836 0.01061 0.00496 -0.1596 0.4471 0.6129
2.750 1.2127 0.01060 0.00503 -0.1599 0.4465 0.6557
3.000 1.2416 0.01062 0.00513 -0.1602 0.4458 0.7002
3.250 1.2703 0.01066 0.00526 -0.1604 0.4451 0.7488
3.750 1.3230 0.01062 0.00552 -0.1599 0.4441 0.8827
4.000 1.3457 0.01050 0.00553 -0.1587 0.4437 1.0000
4.250 1.3744 0.01056 0.00560 -0.1590 0.4431 1.0000
4.500 1.4030 0.01062 0.00566 -0.1593 0.4424 1.0000
4.750 1.4316 0.01068 0.00573 -0.1595 0.4415 1.0000
5.000 1.4601 0.01075 0.00580 -0.1598 0.4406 1.0000
5.250 1.4885 0.01082 0.00589 -0.1601 0.4397 1.0000
5.500 1.5168 0.01088 0.00596 -0.1603 0.4388 1.0000
5.750 1.5451 0.01095 0.00603 -0.1606 0.4378 1.0000
6.000 1.5733 0.01100 0.00609 -0.1609 0.4368 1.0000
6.250 1.6016 0.01103 0.00613 -0.1611 0.4358 1.0000
6.500 1.6297 0.01105 0.00616 -0.1614 0.4347 1.0000
6.750 1.6577 0.01107 0.00618 -0.1616 0.4336 1.0000
7.000 1.6854 0.01112 0.00623 -0.1618 0.4326 1.0000
7.250 1.7130 0.01119 0.00632 -0.1620 0.4315 1.0000
7.500 1.7405 0.01130 0.00647 -0.1623 0.4300 1.0000
7.750 1.7681 0.01138 0.00661 -0.1625 0.4278 1.0000
8.000 1.7956 0.01143 0.00669 -0.1627 0.4251 1.0000
8.250 1.8231 0.01142 0.00670 -0.1630 0.4221 1.0000
8.500 1.8504 0.01141 0.00669 -0.1631 0.4185 1.0000
8.750 1.8774 0.01143 0.00673 -0.1633 0.4122 1.0000
9.000 1.9032 0.01147 0.00674 -0.1633 0.4051 1.0000
9.250 1.9273 0.01164 0.00687 -0.1630 0.3967 1.0000
9.500 1.9504 0.01190 0.00712 -0.1626 0.3889 1.0000
9.750 1.9715 0.01228 0.00746 -0.1619 0.3811 1.0000
10.000 1.9937 0.01260 0.00779 -0.1614 0.3748 1.0000
10.500 2.0355 0.01334 0.00854 -0.1600 0.3644 1.0000
10.750 2.0544 0.01377 0.00898 -0.1590 0.3585 1.0000
11.000 2.0722 0.01423 0.00944 -0.1578 0.3533 1.0000
11.250 2.0901 0.01464 0.00989 -0.1567 0.3483 1.0000
11.500 2.1028 0.01517 0.01043 -0.1547 0.3436 1.0000
11.750 2.1145 0.01566 0.01095 -0.1524 0.3398 1.0000
12.000 2.1265 0.01616 0.01150 -0.1504 0.3358 1.0000
12.250 2.1332 0.01687 0.01224 -0.1476 0.3312 1.0000
12.500 2.1358 0.01778 0.01318 -0.1445 0.3269 1.0000
12.750 2.1403 0.01868 0.01414 -0.1418 0.3225 1.0000
13.000 2.1352 0.02014 0.01566 -0.1385 0.3180 1.0000
13.250 2.1112 0.02318 0.01877 -0.1344 0.3136 1.0000
13.500 2.0859 0.02763 0.02336 -0.1325 0.3095 1.0000
13.750 1.9835 0.04046 0.03638 -0.1291 0.3018 1.0000
14.000 1.9237 0.04866 0.04467 -0.1267 0.2960 1.0000
14.250 1.8883 0.05462 0.05068 -0.1253 0.2897 1.0000
14.500 1.8645 0.05979 0.05588 -0.1246 0.2840 1.0000
14.750 1.8582 0.06324 0.05936 -0.1243 0.2785 1.0000
15.000 1.8408 0.06804 0.06416 -0.1240 0.2715 1.0000
15.250 1.8397 0.07104 0.06720 -0.1240 0.2656 1.0000
15.500 1.8304 0.07503 0.07117 -0.1240 0.2580 1.0000
15.750 1.8294 0.07812 0.07427 -0.1241 0.2514 1.0000
16.000 1.8188 0.08246 0.07860 -0.1242 0.2439 1.0000
16.250 1.8215 0.08514 0.08130 -0.1244 0.2376 1.0000
16.500 1.8148 0.08906 0.08520 -0.1247 0.2299 1.0000
16.750 1.8117 0.09261 0.08877 -0.1250 0.2228 1.0000
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Polar data table (+)
Polar graphs
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